Airworthiness Directives; Airbus Model A300 B4-600, B4-600R, and F4-600R Series Airplanes, and Model A300 C4-605R Variant F Airplanes (Collectively Called A300-600 Series Airplanes), 35575-35578 [E6-9715]

Download as PDF Federal Register / Vol. 71, No. 119 / Wednesday, June 21, 2006 / Proposed Rules rwilkins on PROD1PC63 with PROPOSAL applicable, as appropriates sources of service information for inspecting MLG DSUs. (h) If any tube having P/N 200485300 with a straight bore is found installed during the inspections required by paragraph (g) of this AD: Before further flight, re-identify the DSU with P/N 200261004, 200485004, or 200684004, in accordance with the Accomplishment Instructions of Dowty Aerospace Landing Gear Service Bulletin 32– 82W, Revision 2, including Appendix A, dated July 29, 1994, and including Appendix B, Revision 1, dated November 10, 1993; or Dowty Aerospace Landing Gear Service Bulletin 32–169B, Revision 2, including Appendix A, dated July 29, 1994, and including Appendix B, Revision 1, dated November 10, 1993; as applicable. After reidentifying the DSU, no further action is required by this AD for that DSU; however airplanes are still subject to the requirements specified in paragraph (k) of this AD. (i) If any tube having P/N 200259300 with a change in section (stepped bore) is found installed during the inspection required by paragraph (g) of this AD: Before further flight, re-identify the DSU in accordance with paragraphs 2.A.(4)(a) and 2.A.(4)(b) of the Accomplishment Instructions Dowty Aerospace Landing Gear Service Bulletin 32– 82W, Revision 2, including Appendix A, dated July 29, 1994, and including Appendix B, Revision 1, dated November 10, 1993; or Dowty Aerospace Landing Gear Service Bulletin 32–169B, Revision 2, including Appendix A, dated July 29, 1994, and including Appendix B, Revision 1, dated November 10, 1993; as applicable. Following accomplishment of the re-identification, before further flight, do the inspection specified in paragraph (j) of this AD. Ultrasonic Inspection for Cracking (j) For airplanes equipped with reidentified DSUs having 200261002, 200485002, 200684002, 200261003, 200485003, or 200684003: Within 60 days after the effective date of this AD, perform an ultrasonic inspection to detect cracking in the re-identified DSUs, in accordance with the Accomplishment Instructions of Dowty Aerospace Landing Gear Service Bulletin 32– 82W, Revision 2, including Appendix A, dated July 29, 1994, and including Appendix B, Revision 1, dated November 10, 1993; or Dowty Aerospace Landing Gear Service Bulletin 32–169B, Revision 2, including Appendix A, dated July 29, 1994, and including Appendix B, Revision 1, dated November 10, 1993; as applicable. (1) For airplanes equipped with any DSU re-identified as P/N 200684003, 200261003, or 200485003: If no crack is detected, no further action is required by this AD for that DSU; however airplanes are still subject to the requirements specified in paragraph (k) of this AD. (2) For airplanes equipped with any DSU re-identified as P/N 200684002, 200261002, or 200485002: If no crack is detected, do the actions specified in paragraphs (j)(2)(i) and (j)(2)(ii) of this AD. (i) Repeat the ultrasonic inspection required by paragraph (j) of this AD thereafter at intervals not to exceed 1,500 flight cycles until the actions specified in paragraph (j)(2)(ii) of this AD are done. VerDate Aug<31>2005 16:40 Jun 20, 2006 Jkt 208001 (ii) At the next MLG overhaul but no later than 12,000 flight cycles after the effective date of this AD, rework and re-identify the DSU as P/N 200261003, 200485003, or 200684003, as applicable, in accordance with the applicable service bulletin. (3) If any crack is detected and the crack signal indication of any DSU tube is greater than or equal to 80 percent, before further flight, replace the DSU with a re-identified DSU having P/N 200261004, 200485004, 200684004, 200261003, 200485003, or 200684003, in accordance with the applicable service bulletin. (4) If any crack is detected and the crack signal indication of any DSU tube is greater than zero percent but less than 80 percent, do the actions specified in paragraphs (j)(4)(i) and (j)(4)(ii) of this AD. (i) Repeat the ultrasonic inspection required by paragraph (j) of this AD thereafter at intervals not to exceed 1,500 flight cycles until the actions specified in paragraph (j)(4)(ii) of this AD are done. (ii) At the next MLG overhaul but no later than 12,000 flight cycles after the effective date of this AD, replace the DSU with a DSU having P/N 200261004, 200485004, 200684004, 200261003, 200485003, or 200684003, in accordance with the applicable service bulletin. 35575 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2006–25088; Directorate Identifier 2006 NM–085–AD] RIN 2120–AA64 Airworthiness Directives; Airbus Model A300 B4–600, B4–600R, and F4–600R Series Airplanes, and Model A300 C4– 605R Variant F Airplanes (Collectively Called A300–600 Series Airplanes) Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Notice of proposed rulemaking (NPRM). AGENCY: SUMMARY: The FAA proposes to supersede an existing airworthiness directive (AD) that applies to certain Airbus Model A300–600 series airplanes. The existing AD currently requires an inspection for evidence of chafing between the hydraulic flexible hose and the ram air turbine (RAT) hub, and related investigative and corrective actions if necessary. This proposed AD would extend the applicability to Parts Installation include all A300–600 series airplanes (k) As of the effective date of this AD, no that are equipped with a certain RAT. person may install a MLG DSU, P/N This proposed AD results from reports 200261001, 200261002, 200485001, of holes in the RAT hub cover. We are 200485002, 200684001, or 200684002, on any proposing this AD to prevent a hole in airplane, except as specified in paragraph (i) the RAT hub cover. A hole in the RAT of this AD. hub cover could allow water to enter the RAT governing mechanism, freeze Alternative Methods of Compliance (AMOCs) during flight, and jam the governing mechanism. In addition, the metal (l)(1) The Manager, International Branch, particles that result from chafing ANM–116, Transport Airplane Directorate, between the hydraulic flexible hose and FAA, has the authority to approve AMOCs the RAT could mix with the lubricant for this AD, if requested in accordance with grease and degrade the governing the procedures found in 14 CFR 39.19. mechanism. In an emergency, a jammed (2) Before using any AMOC approved in or degraded RAT could result in its accordance with § 39.19 on any airplane to failure to deploy, loss of hydraulic which the AMOC applies, notify the pressure or electrical power to the appropriate principal inspector in the FAA airplane, and consequent reduced Flight Standards Certificate Holding District controllability of the airplane. Office. DATES: We must receive comments on Related Information this proposed AD by July 21, 2006. (m) Dutch airworthiness directive NL– ADDRESSES: Use one of the following 2005–003, dated April 29, 2005, also addresses to submit comments on this addresses the subject of this AD. proposed AD. • DOT Docket Web site: Go to Issued in Renton, Washington, on June 14, http://dms.dot.gov and follow the 2006. instructions for sending your comments Kalene C. Yanamura, electronically. Acting Manager, Transport Airplane • Government-wide rulemaking Web Directorate, Aircraft Certification Service. site: Go to http://www.regulations.gov [FR Doc. E6–9714 Filed 6–20–06; 8:45 am] and follow the instructions for sending BILLING CODE 4910–13–P your comments electronically. • Mail: Docket Management Facility; U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL–401, Washington, DC 20590. PO 00000 Frm 00015 Fmt 4702 Sfmt 4702 E:\FR\FM\21JNP1.SGM 21JNP1 35576 Federal Register / Vol. 71, No. 119 / Wednesday, June 21, 2006 / Proposed Rules • Fax: (202) 493–2251. • Hand Delivery: Room PL–401 on the plaza level of the Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France, for service information identified in this proposed AD. FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98055–4056; telephone (425) 227–2125; fax (425) 227–1149. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to submit any relevant written data, views, or arguments regarding this proposed AD. Send your comments to an address listed in the ADDRESSES section. Include the docket number ‘‘Docket No. FAA–2006–25088; Directorate Identifier 2006–NM–085– AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the proposed AD. We will consider all comments received by the closing date and may amend the proposed AD in light of those comments. We will post all comments we receive, without change, to http:// dms.dot.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact with FAA personnel concerning this proposed AD. Using the search function of that web site, anyone can find and read the comments in any of our dockets, including the name of the individual who sent the comment (or signed the comment on behalf of an association, business, labor union, etc.). You may review the DOT’s complete Privacy Act Statement in the Federal Register published on April 11, 2000 (65 FR 19477–78), or you may visit http:// dms.dot.gov. rwilkins on PROD1PC63 with PROPOSAL Examining the Docket You may examine the AD docket on the Internet at http://dms.dot.gov, or in person at the Docket Management Facility office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket VerDate Aug<31>2005 16:40 Jun 20, 2006 Jkt 208001 Management Facility office (telephone (800) 647–5227) is located on the plaza level of the Nassif Building at the DOT street address stated in the ADDRESSES section. Comments will be available in the AD docket shortly after the Docket Management System receives them. Discussion On July 11, 2005, we issued AD 2005– 15–05, amendment 39–14194 (70 FR 42267, July 22, 2005), for certain Airbus Model A300–600 series airplanes. That AD requires an inspection for evidence of chafing between the hydraulic flexible hose and the ram air turbine (RAT) hub, and related investigative and corrective actions if necessary. That AD resulted from reports of holes in the RAT hub cover. We issued that AD to prevent a hole in the RAT hub cover. A hole in the RAT hub cover could allow water to enter the RAT governing mechanism, freeze during flight, and jam the governing mechanism. In addition, the metal particles that result from chafing between the hydraulic flexible hose and the RAT could mix with the lubricant grease and degrade the governing mechanism. In an emergency, a jammed or degraded RAT could result in its failure to deploy, loss of hydraulic pressure or electrical power to the airplane, and consequent reduced controllability of the airplane. Actions Since Existing AD Was Issued Since we issued AD 2005–15–05, the ´ ´ Direction Generale de l’Aviation Civile (DGAC), which is the airworthiness authority for France, reported that a hole in the RAT hub cover was reported on an airplane that was not included in the effectivity of French airworthiness directive F–2004–133, dated August 4, 2004. French airworthiness directive F– 2004–133 parallels AD 2005–15–05. Relevant Service Information Airbus has issued Service Bulletin A300–29–6054, Revision 02, dated January 12, 2006. Airbus Service Bulletin A300–29–6054, Revision 01, excluding Appendix 01, dated November 4, 2004, was referenced as the appropriate source of service information for doing the action required by AD 2005–15–05. The procedures in Revision 02 and Revision 01 are essentially the same. Revision 02 extends the effectivity to include all A300–600 series airplanes that are PO 00000 Frm 00016 Fmt 4702 Sfmt 4702 equipped with a Hamilton Sundstrand RAT. Accomplishing the actions specified in the service information is intended to adequately address the unsafe condition. The FCAA mandated the service information and issued French airworthiness directive F–2006– 035, dated February 1, 2006, to ensure the continued airworthiness of these airplanes in France. FAA’s Determination and Requirements of the Proposed AD These airplane models are manufactured in France and are type certificated for operation in the United States under the provisions of section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and the applicable bilateral airworthiness agreement. Pursuant to this bilateral airworthiness agreement, the DGAC has kept the FAA informed of the situation described above. We have examined the DGAC’s findings, evaluated all pertinent information, and determined that AD action is necessary for airplanes of this type design that are certificated for operation in the United States. This proposed AD would supersede AD 2005–15–05 and would retain the requirements of the existing AD. This proposed AD would also add airplanes to the applicability. 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. Explanation of Change to Costs of Compliance After the original NPRM was issued, we reviewed the figures we have used over the past several years to calculate AD costs to operators. To account for various inflationary costs in the airline industry, we find it necessary to increase the labor rate used in these calculations from $65 per work hour to $80 per work hour. The cost impact information, below, reflects this increase in the specified hourly labor rate. Costs of Compliance The following table provides the estimated costs for U.S. operators to comply with this proposed AD. E:\FR\FM\21JNP1.SGM 21JNP1 Federal Register / Vol. 71, No. 119 / Wednesday, June 21, 2006 / Proposed Rules 35577 ESTIMATED COSTS Action Average labor rate per hour Work hours Inspection (required by AD 2005–15–05) ............................ Rework binding (required by AD 2005–15–05) ................... 1 1 $80 80 The Proposed Amendment 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. Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: Regulatory Findings rwilkins on PROD1PC63 with PROPOSAL Authority for This Rulemaking (a) The FAA must receive comments on this AD action by July 21, 2006. We have determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would 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 the proposed regulation: 1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866; 2. Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and 3. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. We prepared a regulatory evaluation of the estimated costs to comply with this proposed 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, Safety. VerDate Aug<31>2005 16:40 Jun 20, 2006 Jkt 208001 PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The Federal Aviation Administration (FAA) amends § 39.13 by removing amendment 39–14194 (70 FR 42267, July 22, 2005) and adding the following new airworthiness directive (AD): Airbus: Docket No. FAA–2006–25088; Directorate Identifier 2006–NM–085–AD. Comments Due Date Affected ADs (b) This AD supersedes AD 2005–15–05. Applicability (c) This AD applies to Airbus Model A300 B4–601, B4–603, B4–620, B4–622, B4–605R, B4–622R, F4–605R, F4–622R, and C4–605R Variant F airplanes; certificated in any category; equipped with a Hamilton Sundstrand Ram Air Turbine (RAT). Unsafe Condition (d) This AD results from reports of holes in the ram air turbine (RAT) hub cover. We are issuing this AD to prevent a hole in the RAT hub cover. A hole in the RAT hub cover could allow water to enter the RAT governing mechanism, freeze during flight, and jam the governing mechanism. In addition, the metal particles that result from chafing between the hydraulic flexible hose and the RAT could mix with the lubricant grease and degrade the governing mechanism. In an emergency, a jammed or degraded RAT could result in its failure to deploy, loss of hydraulic pressure or electrical power to the airplane, and consequent 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. PO 00000 Frm 00017 Fmt 4702 Sfmt 4702 Cost per airplane $80 80 Number of U.S.-registered airplanes 120 120 Fleet cost $9,600 9,600 Restatement of the Requirements of AD 2005–15–05 With Compliance Times for New Airplanes Inspection and Related Investigative/ Corrective Actions (f) At the applicable time specified in paragraph (f)(1) or (f)(2) of this AD: Do a onetime detailed inspection for evidence of chafing between the hydraulic flexible hose and the RAT hub, and any applicable related investigative and corrective actions, by accomplishing all of the applicable actions specified in the Accomplishment Instructions of Airbus Service Bulletin A300– 29–6054, Revision 01, excluding Appendix 01, dated November 4, 2004; or Revision 02, dated January 12, 2006. After the effective date of this AD, only Revision 02 may be used. Any applicable corrective actions must be accomplished before further flight. Where the service bulletin specifies to submit certain information to the manufacturer, and to submit damaged RATs to the vendor or a repair station, this AD does not include those requirements. (1) For airplanes having serial numbers (S/ Ns) 0812, 0813, 0815 through 0818 inclusive, 0821 through 0828 inclusive, and 0836 through 0838 inclusive: Within 2,500 flight hours after August 26, 2005 (the effective date of AD 2005–15–05). (2) For airplanes not identified in paragraph (f)(1) of this AD: Within 2,500 flight hours after the effective date of this AD. Note 1: 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.’’ Actions Accomplished Previously (g) Actions accomplished before the effective date of this AD, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300–29–6054, excluding Appendix 01, dated June 8, 2004, are acceptable for compliance with the corresponding actions specified in this AD. Alternative Methods of Compliance (AMOCs) (h)(1) The Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19. (2) Before using any AMOC approved in accordance with § 39.19 on any airplane to which the AMOC applies, notify the E:\FR\FM\21JNP1.SGM 21JNP1 35578 Federal Register / Vol. 71, No. 119 / Wednesday, June 21, 2006 / Proposed Rules appropriate principal inspector in the FAA Flight Standards Certificate Holding District Office. (3) AMOCs approved previously in accordance with AD 2005–15–05 are approved as AMOCs for the corresponding provisions of this AD. Related Information (i) French airworthiness directive F–2006– 035, dated February 1, 2006, also addresses the subject of this AD. Issued in Renton, Washington, on June 14, 2006. Kalene C. Yanamura, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E6–9715 Filed 6–20–06; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2006–25089; Directorate Identifier 2006–NM–091–AD] RIN 2120–AA64 Airworthiness Directives; McDonnell Douglas Model MD–11 and –11F Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Notice of proposed rulemaking (NPRM). rwilkins on PROD1PC63 with PROPOSAL AGENCY: SUMMARY: The FAA proposes to supersede an existing airworthiness directive (AD) that applies to certain McDonnell Douglas Model MD–11 and –11F airplanes. The existing AD currently requires an initial general visual inspection of the power feeder cables of the integrated drive generator (IDG) and the fuel feed lines of engine pylons No. 1 and No. 3 on the wings for proper clearance and damage; corrective actions if necessary; and repetitive general visual inspections and a terminating action for the repetitive inspections. This proposed AD would continue to require the existing actions, and for certain airplanes, this proposed AD would require installation of new clamps on the power feeder cables of the IDG of engine pylons No. 1 and No. 3. This proposed AD results from reports of IDG power feeder cables riding against structure and fuel lines in the No. 1 and No. 3 pylons. We are proposing this AD to prevent potential chafing of the power feeder cables of the IDG in engine pylons No. 1 and No. 3 on the wings, and consequent arcing on the fuel lines in the engine pylons and possible fuel fire. VerDate Aug<31>2005 16:40 Jun 20, 2006 Jkt 208001 We must receive comments on this proposed AD by August 7, 2006. ADDRESSES: Use one of the following addresses to submit comments on this proposed AD. • DOT Docket Web site: Go to http:// dms.dot.gov and follow the instructions for sending your comments electronically. • Government-wide rulemaking Web site: Go to http://www.regulations.gov and follow the instructions for sending your comments electronically. • Mail: Docket Management Facility; U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL–401, Washington, DC 20590. • Fax: (202) 493–2251. • Hand Delivery: Room PL–401 on the plaza level of the Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. Contact Boeing Commercial Airplanes, Long Beach Division, 3855 Lakewood Boulevard, Long Beach, California 90846, Attention: Data and Service Management, Dept. C1–L5A (D800–0024), for service information identified in this proposed AD. FOR FURTHER INFORMATION CONTACT: Brett Portwood, Aerospace Engineer, Systems and Equipment Branch, ANM– 130L, FAA, Los Angeles Aircraft Certification Office, 3960 Paramount Boulevard, Lakewood, California 90712; telephone (562) 627–5350; fax (562) 627–5210. SUPPLEMENTARY INFORMATION: DATES: Comments Invited We invite you to submit any relevant written data, views, or arguments regarding this proposed AD. Send your comments to an address listed in the ADDRESSES section. Include the docket number ‘‘Docket No. FAA–2006–25089; Directorate Identifier 2006–NM–091– AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the proposed AD. We will consider all comments received by the closing date and may amend the proposed AD in light of those comments. We will post all comments we receive, without change, to http:// dms.dot.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact with FAA personnel concerning this proposed AD. Using the search function of that web site, anyone can find and read the comments in any of our dockets, including the name of the individual who sent the comment (or signed the PO 00000 Frm 00018 Fmt 4702 Sfmt 4702 comment on behalf of an association, business, labor union, etc.). You may review the DOT’s complete Privacy Act Statement in the Federal Register published on April 11, 2000 (65 FR 19477–78), or may can visit http:// dms.dot.gov. Examining the Docket You may examine the AD docket on the Internet at http://dms.dot.gov, or in person at the Docket Management Facility office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Management Facility office (telephone (800) 647–5227) is located on the plaza level of the Nassif Building at the DOT street address stated in the ADDRESSES section. Comments will be available in the AD docket shortly after the Docket Management System receives them. Discussion On January 2, 2004, we issued AD 2004–01–17, amendment 39–13431 (69 FR 2657, January 20, 2004), for certain McDonnell Douglas Model MD–11 and –11F airplanes. That AD requires an initial general visual inspection of the power feeder cables of the integrated drive generator (IDG) and the fuel feed lines of engine pylons No. 1 and No. 3 on the wings for proper clearance and damage; corrective actions if necessary; and repetitive general visual inspections and a terminating action for the repetitive inspections. That AD resulted from the FAA’s practice of re-examining all aspects of the service experience of a particular aircraft whenever an accident occurs. We became aware of reports indicating that the power feeder cables of the integrated drive generator (IDG) are riding against structure and fuel lines in engine pylons No. 1 and No. 3 on the wings of certain McDonnell Douglas Model MD–11 and –11F airplanes. We issued that AD to prevent potential chafing of the power feeder cables of the IDG in engine pylons No. 1 and No. 3 on the wings, and consequent arcing of the fuel lines in the engine pylons and possible fuel fire. Actions Since Existing AD Was Issued Since we issued AD 2004–01–17, the manufacturer has notified us that certain airplanes with 4/0 size cables installed have clamps too small to install over the 4/0 size cables. Those airplanes need to have larger clamps installed. The larger clamps are needed to prevent chafing of the larger power feeder cables of the IDG. Relevant Service Information We have reviewed Boeing Alert Service Bulletin (ASB) MD11–54A011, E:\FR\FM\21JNP1.SGM 21JNP1

Agencies

[Federal Register Volume 71, Number 119 (Wednesday, June 21, 2006)]
[Proposed Rules]
[Pages 35575-35578]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E6-9715]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-25088; Directorate Identifier 2006 NM-085-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A300 B4-600, B4-600R, and 
F4-600R Series Airplanes, and Model A300 C4-605R Variant F Airplanes 
(Collectively Called A300-600 Series Airplanes)

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

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: The FAA proposes to supersede an existing airworthiness 
directive (AD) that applies to certain Airbus Model A300-600 series 
airplanes. The existing AD currently requires an inspection for 
evidence of chafing between the hydraulic flexible hose and the ram air 
turbine (RAT) hub, and related investigative and corrective actions if 
necessary. This proposed AD would extend the applicability to include 
all A300-600 series airplanes that are equipped with a certain RAT. 
This proposed AD results from reports of holes in the RAT hub cover. We 
are proposing this AD to prevent a hole in the RAT hub cover. A hole in 
the RAT hub cover could allow water to enter the RAT governing 
mechanism, freeze during flight, and jam the governing mechanism. In 
addition, the metal particles that result from chafing between the 
hydraulic flexible hose and the RAT could mix with the lubricant grease 
and degrade the governing mechanism. In an emergency, a jammed or 
degraded RAT could result in its failure to deploy, loss of hydraulic 
pressure or electrical power to the airplane, and consequent reduced 
controllability of the airplane.

DATES: We must receive comments on this proposed AD by July 21, 2006.

ADDRESSES: Use one of the following addresses to submit comments on 
this proposed AD.
     DOT Docket Web site: Go to http://dms.dot.gov and follow 
the instructions for sending your comments electronically.
     Government-wide rulemaking Web site: Go to http://
www.regulations.gov and follow the instructions for sending your 
comments electronically.
     Mail: Docket Management Facility; U.S. Department of 
Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401, 
Washington, DC 20590.

[[Page 35576]]

     Fax: (202) 493-2251.
     Hand Delivery: Room PL-401 on the plaza level of the 
Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, 
France, for service information identified in this proposed AD.

FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
227-2125; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to submit any relevant written data, views, or 
arguments regarding this proposed AD. Send your comments to an address 
listed in the ADDRESSES section. Include the docket number ``Docket No. 
FAA-2006-25088; Directorate Identifier 2006-NM-085-AD'' at the 
beginning of your comments. We specifically invite comments on the 
overall regulatory, economic, environmental, and energy aspects of the 
proposed AD. We will consider all comments received by the closing date 
and may amend the proposed AD in light of those comments.
    We will post all comments we receive, without change, to http://
dms.dot.gov, including any personal information you provide. We will 
also post a report summarizing each substantive verbal contact with FAA 
personnel concerning this proposed AD. Using the search function of 
that web site, anyone can find and read the comments in any of our 
dockets, including the name of the individual who sent the comment (or 
signed the comment on behalf of an association, business, labor union, 
etc.). You may review the DOT's complete Privacy Act Statement in the 
Federal Register published on April 11, 2000 (65 FR 19477-78), or you 
may visit http://dms.dot.gov.

Examining the Docket

    You may examine the AD docket on the Internet at http://
dms.dot.gov, or in person at the Docket Management Facility office 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The Docket Management Facility office (telephone (800) 647-
5227) is located on the plaza level of the Nassif Building at the DOT 
street address stated in the ADDRESSES section. Comments will be 
available in the AD docket shortly after the Docket Management System 
receives them.

Discussion

    On July 11, 2005, we issued AD 2005-15-05, amendment 39-14194 (70 
FR 42267, July 22, 2005), for certain Airbus Model A300-600 series 
airplanes. That AD requires an inspection for evidence of chafing 
between the hydraulic flexible hose and the ram air turbine (RAT) hub, 
and related investigative and corrective actions if necessary. That AD 
resulted from reports of holes in the RAT hub cover. We issued that AD 
to prevent a hole in the RAT hub cover. A hole in the RAT hub cover 
could allow water to enter the RAT governing mechanism, freeze during 
flight, and jam the governing mechanism. In addition, the metal 
particles that result from chafing between the hydraulic flexible hose 
and the RAT could mix with the lubricant grease and degrade the 
governing mechanism. In an emergency, a jammed or degraded RAT could 
result in its failure to deploy, loss of hydraulic pressure or 
electrical power to the airplane, and consequent reduced 
controllability of the airplane.

Actions Since Existing AD Was Issued

    Since we issued AD 2005-15-05, the Direction G[eacute]n[eacute]rale 
de l'Aviation Civile (DGAC), which is the airworthiness authority for 
France, reported that a hole in the RAT hub cover was reported on an 
airplane that was not included in the effectivity of French 
airworthiness directive F-2004-133, dated August 4, 2004. French 
airworthiness directive F-2004-133 parallels AD 2005-15-05.

Relevant Service Information

    Airbus has issued Service Bulletin A300-29-6054, Revision 02, dated 
January 12, 2006. Airbus Service Bulletin A300-29-6054, Revision 01, 
excluding Appendix 01, dated November 4, 2004, was referenced as the 
appropriate source of service information for doing the action required 
by AD 2005-15-05. The procedures in Revision 02 and Revision 01 are 
essentially the same. Revision 02 extends the effectivity to include 
all A300-600 series airplanes that are equipped with a Hamilton 
Sundstrand RAT. Accomplishing the actions specified in the service 
information is intended to adequately address the unsafe condition. The 
FCAA mandated the service information and issued French airworthiness 
directive F-2006-035, dated February 1, 2006, to ensure the continued 
airworthiness of these airplanes in France.

FAA's Determination and Requirements of the Proposed AD

    These airplane models are manufactured in France and are type 
certificated for operation in the United States under the provisions of 
section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and 
the applicable bilateral airworthiness agreement. Pursuant to this 
bilateral airworthiness agreement, the DGAC has kept the FAA informed 
of the situation described above. We have examined the DGAC's findings, 
evaluated all pertinent information, and determined that AD action is 
necessary for airplanes of this type design that are certificated for 
operation in the United States.
    This proposed AD would supersede AD 2005-15-05 and would retain the 
requirements of the existing AD. This proposed AD would also add 
airplanes to the applicability.

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.

Explanation of Change to Costs of Compliance

    After the original NPRM was issued, we reviewed the figures we have 
used over the past several years to calculate AD costs to operators. To 
account for various inflationary costs in the airline industry, we find 
it necessary to increase the labor rate used in these calculations from 
$65 per work hour to $80 per work hour. The cost impact information, 
below, reflects this increase in the specified hourly labor rate.

Costs of Compliance

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

[[Page 35577]]



                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                  Number of U.S.-
             Action                 Work hours     Average labor     Cost per       registered      Fleet cost
                                                   rate per hour     airplane        airplanes
----------------------------------------------------------------------------------------------------------------
Inspection (required by AD 2005-               1             $80             $80             120          $9,600
 15-05).........................
Rework binding (required by AD                 1              80              80             120           9,600
 2005-15-05)....................
----------------------------------------------------------------------------------------------------------------

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 proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would 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 the proposed 
regulation:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979); and
    3. Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.
    We prepared a regulatory evaluation of the estimated costs to 
comply with this proposed 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, Safety.

The Proposed Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

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

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


Sec.  39.13  [Amended]

    2. The Federal Aviation Administration (FAA) amends Sec.  39.13 by 
removing amendment 39-14194 (70 FR 42267, July 22, 2005) and adding the 
following new airworthiness directive (AD):

Airbus: Docket No. FAA-2006-25088; Directorate Identifier 2006-NM-
085-AD.

Comments Due Date

    (a) The FAA must receive comments on this AD action by July 21, 
2006.

Affected ADs

    (b) This AD supersedes AD 2005-15-05.

Applicability

    (c) This AD applies to Airbus Model A300 B4-601, B4-603, B4-620, 
B4-622, B4-605R, B4-622R, F4-605R, F4-622R, and C4-605R Variant F 
airplanes; certificated in any category; equipped with a Hamilton 
Sundstrand Ram Air Turbine (RAT).

Unsafe Condition

    (d) This AD results from reports of holes in the ram air turbine 
(RAT) hub cover. We are issuing this AD to prevent a hole in the RAT 
hub cover. A hole in the RAT hub cover could allow water to enter 
the RAT governing mechanism, freeze during flight, and jam the 
governing mechanism. In addition, the metal particles that result 
from chafing between the hydraulic flexible hose and the RAT could 
mix with the lubricant grease and degrade the governing mechanism. 
In an emergency, a jammed or degraded RAT could result in its 
failure to deploy, loss of hydraulic pressure or electrical power to 
the airplane, and consequent 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 the Requirements of AD 2005-15-05 With Compliance Times 
for New Airplanes

Inspection and Related Investigative/Corrective Actions

    (f) At the applicable time specified in paragraph (f)(1) or 
(f)(2) of this AD: Do a one-time detailed inspection for evidence of 
chafing between the hydraulic flexible hose and the RAT hub, and any 
applicable related investigative and corrective actions, by 
accomplishing all of the applicable actions specified in the 
Accomplishment Instructions of Airbus Service Bulletin A300-29-6054, 
Revision 01, excluding Appendix 01, dated November 4, 2004; or 
Revision 02, dated January 12, 2006. After the effective date of 
this AD, only Revision 02 may be used. Any applicable corrective 
actions must be accomplished before further flight. Where the 
service bulletin specifies to submit certain information to the 
manufacturer, and to submit damaged RATs to the vendor or a repair 
station, this AD does not include those requirements.
    (1) For airplanes having serial numbers (S/Ns) 0812, 0813, 0815 
through 0818 inclusive, 0821 through 0828 inclusive, and 0836 
through 0838 inclusive: Within 2,500 flight hours after August 26, 
2005 (the effective date of AD 2005-15-05).
    (2) For airplanes not identified in paragraph (f)(1) of this AD: 
Within 2,500 flight hours after the effective date of this AD.

    Note 1: 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.''

Actions Accomplished Previously

    (g) Actions accomplished before the effective date of this AD, 
in accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A300-29-6054, excluding Appendix 01, dated June 8, 2004, 
are acceptable for compliance with the corresponding actions 
specified in this AD.

Alternative Methods of Compliance (AMOCs)

    (h)(1) The Manager, International Branch, ANM-116, Transport 
Airplane Directorate, FAA, has the authority to approve AMOCs for 
this AD, if requested in accordance with the procedures found in 14 
CFR 39.19.
    (2) Before using any AMOC approved in accordance with Sec.  
39.19 on any airplane to which the AMOC applies, notify the

[[Page 35578]]

appropriate principal inspector in the FAA Flight Standards 
Certificate Holding District Office.
    (3) AMOCs approved previously in accordance with AD 2005-15-05 
are approved as AMOCs for the corresponding provisions of this AD.

Related Information

    (i) French airworthiness directive F-2006-035, dated February 1, 
2006, also addresses the subject of this AD.

    Issued in Renton, Washington, on June 14, 2006.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
 [FR Doc. E6-9715 Filed 6-20-06; 8:45 am]
BILLING CODE 4910-13-P