Airworthiness Directives; Airbus Model A318, A319, A320, and A321 Airplanes, 51164-51167 [E7-17385]

Download as PDF 51164 Federal Register / Vol. 72, No. 172 / Thursday, September 6, 2007 / Rules and Regulations 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 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. (3) An AMOC approved previously in accordance with AD 2005–18–14 is approved as an AMOC for the corresponding provisions of this AD. Related Information (n) European Aviation Safety Agency airworthiness directive 2006–0114, dated May 10, 2006, also addresses the subject of this AD. Material Incorporated by Reference (o) You must use the service bulletins identified in Table 1 of this AD to perform the actions that are required by this AD, unless the AD specifies otherwise. (1) The Director of the Federal Register approved the incorporation by reference of Dassault Service Bulletin F10–313, Revision 1, dated May 10, 2006, in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. (2) On September 26, 2005 (70 FR 53540, September 9, 2005), the Director of the Federal Register approved the incorporation by reference of Dassault Alert Service Bulletin F10–A312, Revision 1, dated June 27, 2005, including the Service Bulletins Compliance Card. (3) On April 26, 2005 (70 FR 18282, April 11, 2005), the Director of the Federal Register approved the incorporation by reference of Dassault Alert Service Bulletin F10–A312, dated February 25, 2005, including the Service Bulletins Compliance Card. (4) Contact Dassault Falcon Jet, P.O. Box 2000, South Hackensack, New Jersey 07606, 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: http://www.archives.gov/federalregister/cfr/ibr-locations.html. TABLE 1.—SERVICE INFORMATION INCORPORATED BY REFERENCE Service Bulletin Revision level Date Dassault Alert Service Bulletin F10–A312, including the Service Bulletins Compliance Card .............. Dassault Alert Service Bulletin F10–A312, including the Service Bulletins Compliance Card .............. Dassault Service Bulletin F10–313 ......................................................................................................... Original .................. Revision 1 .............. Revision 1 .............. February 25, 2005. June 27, 2005. May 10, 2006. pwalker on PROD1PC71 with RULES Issued in Renton, Washington, on August 17, 2007. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E7–17288 Filed 9–5–07; 8:45 am] support, and corrective action if necessary; and a check of the NLG strut inflation pressure, and an adjustment if necessary. For some of these airplanes, the existing AD also requires a revision to the aircraft flight manual to incorporate an operating procedure to BILLING CODE 4910–13–P recover normal steering in the event of a steering failure. This new AD instead DEPARTMENT OF TRANSPORTATION requires repetitive inspections of the NLG upper support, and related Federal Aviation Administration investigative/corrective actions in accordance with new service 14 CFR Part 39 information; and removes the one-time inspection that was required by the [Docket No. FAA–2007–27776; Directorate existing AD. This new AD also provides Identifier 2006–NM–170–AD; Amendment an optional terminating action for the 39–15189; AD 2007–18–09] repetitive inspections. This AD results RIN 2120–AA64 from a report of an incident where an airplane landed with the NLG turned 90 Airworthiness Directives; Airbus Model degrees from centerline, and from A318, A319, A320, and A321 Airplanes additional reports of NLG upper support anti-rotation lugs rupturing in service. AGENCY: Federal Aviation We are issuing this AD to prevent Administration (FAA), Department of landings with the NLG turned 90 Transportation (DOT). degrees from centerline, which could ACTION: Final rule. result in reduced controllability of the airplane. SUMMARY: The FAA is superseding an existing airworthiness directive (AD), DATES: This AD becomes effective which applies to all Airbus Model October 11, 2007. The Director of the Federal Register A318–100, A319–100, A320–200, A321– 100, and A321–200 series airplanes, and approved the incorporation by reference of a certain publication listed in the AD Model A320–111 airplanes. That AD as of October 11, 2007. currently requires an inspection to On November 30, 2005 (70 FR 70715, determine whether certain braking and November 23, 2005), the Director of the steering control units (BSCUs) are Federal Register approved the installed or have ever been installed. incorporation by reference of a certain For airplanes on which certain BSCUs are installed or have ever been installed, publication listed in the AD. the existing AD requires an inspection ADDRESSES: You may examine the AD of the nose landing gear (NLG) upper docket on the Internet at http:// VerDate Aug<31>2005 18:26 Sep 05, 2007 Jkt 211001 PO 00000 Frm 00006 Fmt 4700 Sfmt 4700 dms.dot.gov or in person at the U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC. Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France, for service information identified in this AD. FOR FURTHER INFORMATION CONTACT: Tim Dulin, Aerospace Engineer, International Branch, ANM–116, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 227–2141; fax (425) 227–1149. SUPPLEMENTARY INFORMATION: Examining the Docket You may examine the airworthiness directive (AD) docket on the Internet at http://dms.dot.gov or in person at the Docket Operations office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Operations office (telephone (800) 647– 5527) is located on the ground floor of the West Building at the DOT street address stated in the ADDRESSES section. Discussion The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that supersedes AD 2005–24–06, amendment 39–14386 (70 FR 70715, November 23, 2005). The existing AD applies to all Airbus Model A318–100, A319–100, A320–200, A321–100, and A321–200 series airplanes, and Model A320–111 E:\FR\FM\06SER1.SGM 06SER1 Federal Register / Vol. 72, No. 172 / Thursday, September 6, 2007 / Rules and Regulations airplanes. That NPRM was published in the Federal Register on April 5, 2007 (72 FR 16749). That NPRM proposed to continue to require an inspection to determine whether certain braking and steering control units (BSCUs) are installed or have ever been installed. For airplanes on which certain BSCUs are installed or have ever been installed, that NPRM proposed to continue to require a revision to the aircraft flight manual (AFM) to incorporate an operating procedure to recover normal steering in the event of a steering failure. That NPRM also proposed to require repetitive inspections of the nose landing gear (NLG) upper support, and related investigative/corrective actions, and an optional terminating action for the repetitive inspections. Comments We provided the public the opportunity to participate in the development of this AD. We have considered the comments that have been received on the NPRM. Support for the AD The National Transportation Safety Board supports the adoption of the AD. Request To Revise ‘‘Optional Terminating Action’’ Reference Airbus requests that we rephrase the heading of paragraph (l), ‘‘Optional Terminating Action,’’ of the NPRM. Airbus states that the terminating action for the issue addressed by the NPRM is not yet available. According to Airbus, the terminating action will include implementation of a new BSCU standard, which is currently being defined. Therefore, Airbus suggests that instead of the title ‘‘Optional Terminating Action,’’ we use a different title, such as ‘‘Action that Renders Void the Requirements of this AD,’’ or equivalent wording. Airbus states that it is correct to say that the actions proposed in paragraph (l) of the NPRM would render void the requirements of this AD, and that no further action would be required by this AD. However, the terminating action for the issue will require installation of a new future BSCU standard. Airbus anticipates that it will require the installation of the future BSCU standard as a terminating action. We disagree with the request to rephrase the title of paragraph (l) of this AD. We consider the phrase ‘‘Action that Renders Void the Requirements of this AD,’’ to be equivalent to the existing title ‘‘Optional Terminating Action.’’ Furthermore, this AD is fully consistent with European Aviation Safety Agency (EASA) airworthiness directive 2006–0174, dated June 21, 2006, which is the parallel EASA airworthiness directive to this AD. If EASA supersedes airworthiness directive 2006–0174 for any reason, we will consider additional rulemaking. We have not changed the AD in this regard. 51165 Explanation of Editorial Change to Paragraph (l) Paragraph (l) of the NPRM referred to ‘‘standard L4.1 and L4.5.’’ That paragraph should refer to ‘‘standard L4.1 or L4.5.’’ We have revised paragraph (l) of the final rule accordingly. This change will not affect accomplishment of the optional terminating action. Clarification of Alternative Method of Compliance (AMOC) Paragraph We have revised this action to clarify the appropriate procedure for notifying the principal inspector before using any approved AMOC on any airplane to which the AMOC applies. 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. We have determined that these changes will neither increase the economic burden on any operator nor increase the scope of the AD. Costs of Compliance This AD affects about 720 airplanes of U.S. registry. The following table provides the estimated costs for U.S. operators to comply with this AD. The average labor rate is $80 per work hour. ESTIMATED COSTS Work hours Records review (required by AD 2005–24–06) ............. AFM revision (required by AD 2005–24–06) ................. Special detailed inspection in accordance with new service information (new action). pwalker on PROD1PC71 with RULES Action 1 .................. 1 .................. 1 .................. 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 VerDate Aug<31>2005 18:26 Sep 05, 2007 Jkt 211001 Parts Cost per airplane None None None $80 ..................................... $80 ..................................... $80, per inspection cycle .. 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; PO 00000 Frm 00007 Fmt 4700 Sfmt 4700 Fleet cost $57,600. $57,600. $57,600, per inspection cycle. (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. E:\FR\FM\06SER1.SGM 06SER1 51166 Federal Register / Vol. 72, No. 172 / Thursday, September 6, 2007 / Rules and Regulations not and never has been equipped with a BSCU P/N E21327001 or P/N E21327003, no further action is required by this AD. 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. § 39.13 [Amended] 2. The Federal Aviation Administration (FAA) amends § 39.13 by removing amendment 39–14386 (70 FR 70715, November 23, 2005) and by adding the following new airworthiness directive (AD): I 2007–18–09 AIRBUS: Amendment 39– 15189. Docket No. FAA–2007–27776; Directorate Identifier 2006–NM–170–AD. Effective Date (a) This AD becomes effective October 11, 2007. Affected ADs (b) This AD supersedes AD 2005–24–06. Applicability (c) This AD applies to all Airbus Model A318, A319, A320, and A321 airplanes. Unsafe Condition (d) This AD results from a report of an incident where an airplane landed with the nose landing gear (NLG) turned 90 degrees from centerline, and from additional reports of NLG upper support anti-rotation lugs rupturing in service. We are issuing this AD to prevent landings with the NLG turned 90 degrees from centerline, which could result in reduced controllability 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. pwalker on PROD1PC71 with RULES Restatement of Certain Requirements of AD 2005–24–06 Records Review (f) Within 5 days after November 30, 2005 (the effective date of AD 2005–24–06), perform a records review to determine whether the airplane is equipped with or has ever been equipped with an enhanced manufacturing and maintainability (EMM) braking and steering control unit (BSCU) part number (P/N) E21327001 (standard L4.1, installed by Airbus Modification 26965, or Airbus Service Bulletin A320–32–1912) or P/N E21327003 (standard L4.5, installed by Airbus Modification 33376, or Airbus Service Bulletin A320–32–1261). Airbus Service Bulletin A320–32–1310, dated February 8, 2006, is one approved method for doing the records review. (g) For airplanes on which a records review required by paragraph (f) of this AD conclusively determines that the airplane is VerDate Aug<31>2005 18:26 Sep 05, 2007 Jkt 211001 Airplane Flight Manual (AFM) Revision (h) For airplanes that are not specified in paragraph (g) of this AD and on which Airbus Modification 31152 has not been incorporated in production (i.e., applicable only to aircraft with steering powered by the green hydraulic system): Within 10 days after November 30, 2005, revise the Limitation Section of the Airbus A318/319/320/321 Aircraft Flight Manual (AFM) to include the following information. This may be done by inserting a copy of this AD into the AFM: ‘‘The ECAM message, in case of a nose wheel steering failure, will be worded as follows: —‘‘WHEEL N/W STRG FAULT’’ for aircraft with the FWC E3 and subsequent standards —‘‘WHEEL N.W. STEER FAULT’’ for aircraft with the FWC E2 Standard. I If the L/G SHOCK ABSORBER FAULT ECAM caution is triggered at any time in flight, and the WHEEL N/W STRG FAULT ECAM caution is triggered after the landing gear extension: • When all landing gear doors are indicated closed on ECAM WHEEL page, reset the BSCU: —A/SKID&N/W STRG—OFF THEN ON • If the WHEEL N/W STRG FAULT ECAM caution is no longer displayed, this indicates a successful nose wheel re-centering and steering recovery. —Rearm the AUTO BRAKE, if necessary. • If the WHEEL N/W STRG FAULT ECAM caution remains displayed, this indicates that the nose wheel steering remains lost, and that the nose wheels are not centered. —During landing, delay nose wheel touchdown for as long as possible. —Refer to the ECAM STATUS. I If the WHEEL N/W STRG FAULT ECAM caution appears, without the L/G SHOCK ABSORBER FAULT ECAM caution: —No specific crew action is requested by the WHEEL N/W STRG FAULT ECAM caution procedure. —Refer to the ECAM STATUS.’’ Note 1: When a statement identical to that in paragraph (h) of this AD has been included in the general revisions of the AFM, the general revisions may be inserted into the AFM, and the copy of this AD may be removed from the AFM. New Requirements of This AD Inspection Thresholds (i) For airplanes that are not specified in paragraph (g) of this AD, at the earlier of the times specified in paragraphs (i)(1) and (i)(2) of this AD: Do a special detailed inspection (boroscopic) for broken or cracked NLG upper support lugs and missing cylinder lugs, and do all applicable related investigative/corrective actions before further flight. Do all actions in accordance with Airbus Technical Note 957.1901/05, dated October 18, 2005; or the Accomplishment Instructions of Airbus Service Bulletin A320– 32–1310, dated February 8, 2006. After the PO 00000 Frm 00008 Fmt 4700 Sfmt 4700 effective date of this AD, only Airbus Service Bulletin A320–32–1310, dated February 8, 2006, may be used. Where the service bulletin specifies that restoring the NLG is necessary in accordance with Airbus recommendations, this AD requires restoring the NLG in accordance with 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). Repeat the inspection thereafter at the applicable interval specified in paragraph (j) or (k) of this AD. (1) Within 100 flight cycles following an electronic centralized aircraft monitoring (ECAM) caution ‘‘L/G SHOCK ABSORBER FAULT’’ associated with at least one of the following centralized fault display system (CFDS) messages specified in paragraph (i)(1)(i), (i)(1)(ii), or (i)(1)(iii) of this AD. (i) ‘‘N L/G EXT PROX SNSR 24GA TGT POS.’’ (ii) ‘‘N L/G EXT PROX SNSR 25GA TGT POS.’’ (iii) ‘‘N L/G SHOCK ABSORBER FAULT 2526GM.’’ (2) At the later of the times specified in paragraphs (i)(2)(i) and (i)(2)(ii) of this AD. (i) Within 20 months, 6,000 flight hours, or 4,500 flight cycles since the date of issuance of the original French standard airworthiness certificate, or the original French export certificate of airworthiness, whichever occurs first. (ii) Within 6 months, 1,800 flight hours, or 1,350 flight cycles after the effective date of this AD, whichever occurs first. Repetitive Inspection Intervals (j) For airplanes not specified in paragraph (g) of this AD that are equipped with EMM BSCU standard L4.1 or L4.5: Repeat the inspection specified in paragraph (i) of this AD thereafter at intervals not to exceed the earliest of 6 months; 1,800 flight hours; 1,350 flight cycles; or 100 flight cycles following certain ECAM cautions and CFDS messages, as specified in paragraph (i)(1) of this AD. (k) For airplanes not specified in paragraph (g) of this AD that are equipped with EMM BSCU standard L4.8 or a non-EMM BSCU: Repeat the inspection specified in paragraph (i) of this AD thereafter at intervals not to exceed the earliest of 20 months; 6,000 flight hours; 4,500 flight cycles; or 100 flight cycles following certain ECAM cautions and CFDS messages, as specified in paragraph (i)(1) of this AD. Note 2: For the purposes of this AD, a special detailed inspection is: ‘‘An intensive examination of a specific item, installation, or assembly to detect damage, failure, or irregularity. The examination is likely to make extensive use of specialized inspection techniques and/or equipment. Intricate cleaning and substantial access or disassembly procedure may be required.’’ Optional Terminating Action (l) For airplanes that are not specified in paragraph (g) of this AD: Installation of an NLG with new upper support anti-rotation lugs and new cylinder lugs, or installation of an NLG that was never driven by EMM BSCU standard L4.1 or L4.5; combined with E:\FR\FM\06SER1.SGM 06SER1 Federal Register / Vol. 72, No. 172 / Thursday, September 6, 2007 / Rules and Regulations installation of an EMM BSCU standard L4.8 or a non–EMM BSCU; constitutes terminating action for the requirements of this AD. Do the installations in accordance with a method approved by either the Manager, International Branch, ANM–116; or the EASA (or its delegated agent). Chapter 32 of the Airbus A318/A319/A320/A321 Aircraft Maintenance Manual (AMM) is one approved method for doing the installations. No Report Required (m) Although Airbus Service Bulletin A320–32–1310, dated February 8, 2006, specifies sending certain inspection results to Airbus, this AD does not include that requirement. Credit Paragraph (n) Inspections done before the effective date of this AD in accordance with Chapter 12, Subject 12–14–32 of the Airbus A318/ A319/A320/A321 AMM, as revised by Airbus A318/A319/A320/A321 AMM Temporary Revision 12–001, dated November 13, 2005, are acceptable for compliance with the requirements of paragraph (i) of this AD. Alternative Methods of Compliance (AMOCs) (o)(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) 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. pwalker on PROD1PC71 with RULES Related Information (p) EASA airworthiness directive 2006– 0174, dated June 21, 2006, also addresses the subject of this AD. Material Incorporated by Reference (q) You must use Airbus Technical Note 957.1901/05, dated October 18, 2005; or Airbus Service Bulletin A320–32–1310, dated February 8, 2006; as applicable, to perform the actions that are required by this AD, unless the AD specifies otherwise. (1) The Director of the Federal Register approved the incorporation by reference of Airbus Service Bulletin A320–32–1310, dated February 8, 2006, in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. (2) On November 30, 2005 (70 FR 70715, November 23, 2005), the Director of the Federal Register approved the incorporation by reference of Airbus Technical Note 957.1901/05, dated October 18, 2005. (3) 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; 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: http://www.archives.gov/federal-register/ cfr/ibr-locations.html. VerDate Aug<31>2005 18:26 Sep 05, 2007 Jkt 211001 51167 Issued in Renton, Washington, on August 17, 2007. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E7–17385 Filed 9–5–07; 8:45 am] Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329– 4145; fax: (816) 329–4090. SUPPLEMENTARY INFORMATION: BILLING CODE 4910–13–P We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that would apply to the specified products. That NPRM was published in the Federal Register on July 16, 2007 (72 FR 38800). That NPRM proposed to correct an unsafe condition for the specified products. The MCAI states: DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2007–27975 Directorate Identifier 2007–CE–041–AD; Amendment 39–15187; AD 2007–18–07] RIN 2120–AA64 Airworthiness Directives; Piaggio Aero Industries S.p.A. Model P–180 Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: SUMMARY: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: Several aircraft, at the factory, presented some debris in the hydraulic fluid of the steering system. Investigations revealed that some components of the steering system can be responsible for the fluid contamination because of an initial pollution on their manufacturing. If not corrected, a contaminated fluid could cause malfunction and a possible jamming of the steering system. We are issuing this AD to require actions to correct the unsafe condition on these products. DATES: This AD becomes effective October 11, 2007. On October 11, 2007, the Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD. ADDRESSES: You may examine the AD docket on the Internet at http:// dms.dot.gov or in person at 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: Sarjapur Nagarajan, Aerospace Engineer, FAA, Small Airplane Directorate, 901 PO 00000 Frm 00009 Fmt 4700 Sfmt 4700 Discussion Several aircraft, at the factory, presented some debris in the hydraulic fluid of the steering system. Investigations revealed that some components of the steering system can be responsible for the fluid contamination because of an initial pollution on their manufacturing. If not corrected, a contaminated fluid could cause malfunction and a possible jamming of the steering system. The superseded Airworthiness Directive (AD) 2007–0088–E was previously issued to address the unsafe condition. The present Airworthiness Directive expands applicability of this AD to all P.180 ‘Avanti’ series aircraft and the list of defective components as listed in revision 1 of Piaggio Aero Industries Mandatory Service Bulletin No 80–0236. This AD also requires Temporary Changes to the respective Airplane Flight Manual (AFM) and Aircraft Maintenance Manual (AMM) and introduces procedures to recondition defective units. Comments We gave the public the opportunity to participate in developing this AD. We considered the comment received. Comment Issue: Replacement of Nose Landing Gear One commenter suggests that the nose landing gear (NLG) does not need to be replaced as required in paragraph (f)(2)(ii) of this AD, but rather the steering actuator and manifold mounted to the NLG need to be replaced. We agree with the commenter that it is the steering actuator and the manifold that need to be replaced and not the entire NLG. However, the service bulletin requires removing and sending the original NLG to a Messier-Dowty engineer to do the actuator and manifold replacement. The service bulletin then requires installing a serviceable NLG. The replacement NLG could be the original, which has been rebuilt according to Annex 8 of Piaggio Aero Industries S.p.A. Service Bulletin (Mandatory) N.: 80–0236 Rev. 1, dated May 15, 2007 (Messier-Dowty Service Bulletin No. P180–32–24, dated May 15, 2007), or it could be an exchanged NLG that complies with this AD. We have E:\FR\FM\06SER1.SGM 06SER1

Agencies

[Federal Register Volume 72, Number 172 (Thursday, September 6, 2007)]
[Rules and Regulations]
[Pages 51164-51167]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-17385]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-27776; Directorate Identifier 2006-NM-170-AD; 
Amendment 39-15189; AD 2007-18-09]
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 airworthiness directive 
(AD), which applies to all Airbus Model A318-100, A319-100, A320-200, 
A321-100, and A321-200 series airplanes, and Model A320-111 airplanes. 
That AD currently requires an inspection to determine whether certain 
braking and steering control units (BSCUs) are installed or have ever 
been installed. For airplanes on which certain BSCUs are installed or 
have ever been installed, the existing AD requires an inspection of the 
nose landing gear (NLG) upper support, and corrective action if 
necessary; and a check of the NLG strut inflation pressure, and an 
adjustment if necessary. For some of these airplanes, the existing AD 
also requires a revision to the aircraft flight manual to incorporate 
an operating procedure to recover normal steering in the event of a 
steering failure. This new AD instead requires repetitive inspections 
of the NLG upper support, and related investigative/corrective actions 
in accordance with new service information; and removes the one-time 
inspection that was required by the existing AD. This new AD also 
provides an optional terminating action for the repetitive inspections. 
This AD results from a report of an incident where an airplane landed 
with the NLG turned 90 degrees from centerline, and from additional 
reports of NLG upper support anti-rotation lugs rupturing in service. 
We are issuing this AD to prevent landings with the NLG turned 90 
degrees from centerline, which could result in reduced controllability 
of the airplane.

DATES: This AD becomes effective October 11, 2007.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in the AD as of October 11, 
2007.
    On November 30, 2005 (70 FR 70715, November 23, 2005), the Director 
of the Federal Register approved the incorporation by reference of a 
certain publication listed in the AD.

ADDRESSES: You may examine the AD docket on the Internet at http://
dms.dot.gov or in person at the U.S. Department of Transportation, 
Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 
New Jersey Avenue, SE., Washington, DC.
    Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, 
France, for service information identified in this AD.

FOR FURTHER INFORMATION CONTACT: Tim Dulin, Aerospace Engineer, 
International Branch, ANM-116, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 
227-2141; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION:

Examining the Docket

    You may examine the airworthiness directive (AD) docket on the 
Internet at http://dms.dot.gov or in person at the Docket Operations 
office between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The Docket Operations office (telephone (800) 647-5527) is 
located on the ground floor of the West Building at the DOT street 
address stated in the ADDRESSES section.

Discussion

    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 
CFR part 39 to include an AD that supersedes AD 2005-24-06, amendment 
39-14386 (70 FR 70715, November 23, 2005). The existing AD applies to 
all Airbus Model A318-100, A319-100, A320-200, A321-100, and A321-200 
series airplanes, and Model A320-111

[[Page 51165]]

airplanes. That NPRM was published in the Federal Register on April 5, 
2007 (72 FR 16749). That NPRM proposed to continue to require an 
inspection to determine whether certain braking and steering control 
units (BSCUs) are installed or have ever been installed. For airplanes 
on which certain BSCUs are installed or have ever been installed, that 
NPRM proposed to continue to require a revision to the aircraft flight 
manual (AFM) to incorporate an operating procedure to recover normal 
steering in the event of a steering failure. That NPRM also proposed to 
require repetitive inspections of the nose landing gear (NLG) upper 
support, and related investigative/corrective actions, and an optional 
terminating action for the repetitive inspections.

Comments

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

Support for the AD

    The National Transportation Safety Board supports the adoption of 
the AD.

Request To Revise ``Optional Terminating Action'' Reference

    Airbus requests that we rephrase the heading of paragraph (l), 
``Optional Terminating Action,'' of the NPRM. Airbus states that the 
terminating action for the issue addressed by the NPRM is not yet 
available. According to Airbus, the terminating action will include 
implementation of a new BSCU standard, which is currently being 
defined. Therefore, Airbus suggests that instead of the title 
``Optional Terminating Action,'' we use a different title, such as 
``Action that Renders Void the Requirements of this AD,'' or equivalent 
wording. Airbus states that it is correct to say that the actions 
proposed in paragraph (l) of the NPRM would render void the 
requirements of this AD, and that no further action would be required 
by this AD. However, the terminating action for the issue will require 
installation of a new future BSCU standard. Airbus anticipates that it 
will require the installation of the future BSCU standard as a 
terminating action.
    We disagree with the request to rephrase the title of paragraph (l) 
of this AD. We consider the phrase ``Action that Renders Void the 
Requirements of this AD,'' to be equivalent to the existing title 
``Optional Terminating Action.'' Furthermore, this AD is fully 
consistent with European Aviation Safety Agency (EASA) airworthiness 
directive 2006-0174, dated June 21, 2006, which is the parallel EASA 
airworthiness directive to this AD. If EASA supersedes airworthiness 
directive 2006-0174 for any reason, we will consider additional 
rulemaking. We have not changed the AD in this regard.

Explanation of Editorial Change to Paragraph (l)

    Paragraph (l) of the NPRM referred to ``standard L4.1 and L4.5.'' 
That paragraph should refer to ``standard L4.1 or L4.5.'' We have 
revised paragraph (l) of the final rule accordingly. This change will 
not affect accomplishment of the optional terminating action.

Clarification of Alternative Method of Compliance (AMOC) Paragraph

     We have revised this action to clarify the appropriate procedure 
for notifying the principal inspector before using any approved AMOC on 
any airplane to which the AMOC applies.

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. 
We have determined that these changes will neither increase the 
economic burden on any operator nor increase the scope of the AD.

Costs of Compliance

    This AD affects about 720 airplanes of U.S. registry. The following 
table provides the estimated costs for U.S. operators to comply with 
this AD. The average labor rate is $80 per work hour.

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
              Action                     Work hours          Parts       Cost per airplane        Fleet cost
----------------------------------------------------------------------------------------------------------------
Records review (required by AD     1....................         None  $80.................  $57,600.
 2005-24-06).
AFM revision (required by AD 2005- 1....................         None  $80.................  $57,600.
 24-06).
Special detailed inspection in     1....................         None  $80, per inspection   $57,600, per
 accordance with new service                                            cycle.                inspection cycle.
 information (new action).
----------------------------------------------------------------------------------------------------------------

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.

[[Page 51166]]

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.


Sec.  39.13  [Amended]

0
2. The Federal Aviation Administration (FAA) amends Sec.  39.13 by 
removing amendment 39-14386 (70 FR 70715, November 23, 2005) and by 
adding the following new airworthiness directive (AD):

2007-18-09 AIRBUS: Amendment 39-15189. Docket No. FAA-2007-27776; 
Directorate Identifier 2006-NM-170-AD.

Effective Date

    (a) This AD becomes effective October 11, 2007.

Affected ADs

    (b) This AD supersedes AD 2005-24-06.

Applicability

    (c) This AD applies to all Airbus Model A318, A319, A320, and 
A321 airplanes.

Unsafe Condition

    (d) This AD results from a report of an incident where an 
airplane landed with the nose landing gear (NLG) turned 90 degrees 
from centerline, and from additional reports of NLG upper support 
anti-rotation lugs rupturing in service. We are issuing this AD to 
prevent landings with the NLG turned 90 degrees from centerline, 
which could result in reduced controllability 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 Certain Requirements of AD 2005-24-06

Records Review

    (f) Within 5 days after November 30, 2005 (the effective date of 
AD 2005-24-06), perform a records review to determine whether the 
airplane is equipped with or has ever been equipped with an enhanced 
manufacturing and maintainability (EMM) braking and steering control 
unit (BSCU) part number (P/N) E21327001 (standard L4.1, installed by 
Airbus Modification 26965, or Airbus Service Bulletin A320-32-1912) 
or P/N E21327003 (standard L4.5, installed by Airbus Modification 
33376, or Airbus Service Bulletin A320-32-1261). Airbus Service 
Bulletin A320-32-1310, dated February 8, 2006, is one approved 
method for doing the records review.
    (g) For airplanes on which a records review required by 
paragraph (f) of this AD conclusively determines that the airplane 
is not and never has been equipped with a BSCU P/N E21327001 or P/N 
E21327003, no further action is required by this AD.

Airplane Flight Manual (AFM) Revision

    (h) For airplanes that are not specified in paragraph (g) of 
this AD and on which Airbus Modification 31152 has not been 
incorporated in production (i.e., applicable only to aircraft with 
steering powered by the green hydraulic system): Within 10 days 
after November 30, 2005, revise the Limitation Section of the Airbus 
A318/319/320/321 Aircraft Flight Manual (AFM) to include the 
following information. This may be done by inserting a copy of this 
AD into the AFM:

    ``The ECAM message, in case of a nose wheel steering failure, 
will be worded as follows:

?>--``WHEEL N/W STRG FAULT'' for aircraft with the FWC E3 and 
subsequent standards
--``WHEEL N.W. STEER FAULT'' for aircraft with the FWC E2 Standard.

    [squarf] If the L/G SHOCK ABSORBER FAULT ECAM caution is 
triggered at any time in flight, and the WHEEL N/W STRG FAULT ECAM 
caution is triggered after the landing gear extension:
     When all landing gear doors are indicated closed on 
ECAM WHEEL page, reset the BSCU:

--A/SKID&N/W STRG--OFF THEN ON

     If the WHEEL N/W STRG FAULT ECAM caution is no longer 
displayed, this indicates a successful nose wheel re-centering and 
steering recovery.

--Rearm the AUTO BRAKE, if necessary.

     If the WHEEL N/W STRG FAULT ECAM caution remains 
displayed, this indicates that the nose wheel steering remains lost, 
and that the nose wheels are not centered.

--During landing, delay nose wheel touchdown for as long as 
possible.
--Refer to the ECAM STATUS.

    [squarf] If the WHEEL N/W STRG FAULT ECAM caution appears, 
without the L/G SHOCK ABSORBER FAULT ECAM caution:

--No specific crew action is requested by the WHEEL N/W STRG FAULT 
ECAM caution procedure.
--Refer to the ECAM STATUS.''


    Note 1: When a statement identical to that in paragraph (h) of 
this AD has been included in the general revisions of the AFM, the 
general revisions may be inserted into the AFM, and the copy of this 
AD may be removed from the AFM.

New Requirements of This AD

Inspection Thresholds

    (i) For airplanes that are not specified in paragraph (g) of 
this AD, at the earlier of the times specified in paragraphs (i)(1) 
and (i)(2) of this AD: Do a special detailed inspection (boroscopic) 
for broken or cracked NLG upper support lugs and missing cylinder 
lugs, and do all applicable related investigative/corrective actions 
before further flight. Do all actions in accordance with Airbus 
Technical Note 957.1901/05, dated October 18, 2005; or the 
Accomplishment Instructions of Airbus Service Bulletin A320-32-1310, 
dated February 8, 2006. After the effective date of this AD, only 
Airbus Service Bulletin A320-32-1310, dated February 8, 2006, may be 
used. Where the service bulletin specifies that restoring the NLG is 
necessary in accordance with Airbus recommendations, this AD 
requires restoring the NLG in accordance with 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). Repeat the inspection thereafter at the 
applicable interval specified in paragraph (j) or (k) of this AD.
    (1) Within 100 flight cycles following an electronic centralized 
aircraft monitoring (ECAM) caution ``L/G SHOCK ABSORBER FAULT'' 
associated with at least one of the following centralized fault 
display system (CFDS) messages specified in paragraph (i)(1)(i), 
(i)(1)(ii), or (i)(1)(iii) of this AD.
    (i) ``N L/G EXT PROX SNSR 24GA TGT POS.''
    (ii) ``N L/G EXT PROX SNSR 25GA TGT POS.''
    (iii) ``N L/G SHOCK ABSORBER FAULT 2526GM.''
    (2) At the later of the times specified in paragraphs (i)(2)(i) 
and (i)(2)(ii) of this AD.
    (i) Within 20 months, 6,000 flight hours, or 4,500 flight cycles 
since the date of issuance of the original French standard 
airworthiness certificate, or the original French export certificate 
of airworthiness, whichever occurs first.
    (ii) Within 6 months, 1,800 flight hours, or 1,350 flight cycles 
after the effective date of this AD, whichever occurs first.

Repetitive Inspection Intervals

    (j) For airplanes not specified in paragraph (g) of this AD that 
are equipped with EMM BSCU standard L4.1 or L4.5: Repeat the 
inspection specified in paragraph (i) of this AD thereafter at 
intervals not to exceed the earliest of 6 months; 1,800 flight 
hours; 1,350 flight cycles; or 100 flight cycles following certain 
ECAM cautions and CFDS messages, as specified in paragraph (i)(1) of 
this AD.
    (k) For airplanes not specified in paragraph (g) of this AD that 
are equipped with EMM BSCU standard L4.8 or a non-EMM BSCU: Repeat 
the inspection specified in paragraph (i) of this AD thereafter at 
intervals not to exceed the earliest of 20 months; 6,000 flight 
hours; 4,500 flight cycles; or 100 flight cycles following certain 
ECAM cautions and CFDS messages, as specified in paragraph (i)(1) of 
this AD.

    Note 2: For the purposes of this AD, a special detailed 
inspection is: ``An intensive examination of a specific item, 
installation, or assembly to detect damage, failure, or 
irregularity. The examination is likely to make extensive use of 
specialized inspection techniques and/or equipment. Intricate 
cleaning and substantial access or disassembly procedure may be 
required.''

Optional Terminating Action

    (l) For airplanes that are not specified in paragraph (g) of 
this AD: Installation of an NLG with new upper support anti-rotation 
lugs and new cylinder lugs, or installation of an NLG that was never 
driven by EMM BSCU standard L4.1 or L4.5; combined with

[[Page 51167]]

installation of an EMM BSCU standard L4.8 or a non-EMM BSCU; 
constitutes terminating action for the requirements of this AD. Do 
the installations in accordance with a method approved by either the 
Manager, International Branch, ANM-116; or the EASA (or its 
delegated agent). Chapter 32 of the Airbus A318/A319/A320/A321 
Aircraft Maintenance Manual (AMM) is one approved method for doing 
the installations.

No Report Required

    (m) Although Airbus Service Bulletin A320-32-1310, dated 
February 8, 2006, specifies sending certain inspection results to 
Airbus, this AD does not include that requirement.

Credit Paragraph

    (n) Inspections done before the effective date of this AD in 
accordance with Chapter 12, Subject 12-14-32 of the Airbus A318/
A319/A320/A321 AMM, as revised by Airbus A318/A319/A320/A321 AMM 
Temporary Revision 12-001, dated November 13, 2005, are acceptable 
for compliance with the requirements of paragraph (i) of this AD.

Alternative Methods of Compliance (AMOCs)

    (o)(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) 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

    (p) EASA airworthiness directive 2006-0174, dated June 21, 2006, 
also addresses the subject of this AD.

Material Incorporated by Reference

    (q) You must use Airbus Technical Note 957.1901/05, dated 
October 18, 2005; or Airbus Service Bulletin A320-32-1310, dated 
February 8, 2006; as applicable, to perform the actions that are 
required by this AD, unless the AD specifies otherwise.
    (1) The Director of the Federal Register approved the 
incorporation by reference of Airbus Service Bulletin A320-32-1310, 
dated February 8, 2006, in accordance with 5 U.S.C. 552(a) and 1 CFR 
part 51.
    (2) On November 30, 2005 (70 FR 70715, November 23, 2005), the 
Director of the Federal Register approved the incorporation by 
reference of Airbus Technical Note 957.1901/05, dated October 18, 
2005.
    (3) 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; 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: http://
www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on August 17, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
 [FR Doc. E7-17385 Filed 9-5-07; 8:45 am]
BILLING CODE 4910-13-P