Airworthiness Directives; Boeing Model 767-200, -300, and -400ER Series Airplanes Equipped With Door-Mounted Escape Slides, 34638-34641 [05-11696]

Download as PDF 34638 Federal Register / Vol. 70, No. 114 / Wednesday, June 15, 2005 / Rules and Regulations Affected ADs (b) None. Applicability (c) This AD applies to Airbus Model A319, A320, and A321 series airplanes, certificated in any category; except those on which Airbus Modification 32025 was done during production. Unsafe Condition (d) This AD was prompted by a report of a crack found in the forward lug of the righthand main landing gear (MLG) rib 5 fitting during greasing of the MLG pintle bearings. The FAA is issuing this AD to find and fix cracking in the forward lug of the MLG, which could result in failure of the lug and consequent collapse of the MLG during landing. 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. One-Time Ultrasonic Inspection/Repair (f) For Model A319 and A320 series airplanes having serial numbers 537 through 625 inclusive: At the earliest of the times specified in paragraphs (f)(1), (f)(2), and (f)(3) of this AD; perform a one-time ultrasonic inspection for cracking in the forward lug of the support rib 5 fitting of the left- and righthand MLG by doing all the actions specified in the Accomplishment Instructions of Airbus Service Bulletin A320–57A1136, dated January 26, 2005. Repair any cracking before further flight, according to a method approved by either the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA; or the Direction ´ ´ Generale de l’Aviation Civile (DGAC) (or its delegated agent). (1) Within 750 flight cycles after the effective date of this AD. (2) Within 600 flight hours after the effective date of this AD. (3) Within 100 days after the effective date of this AD. Repetitive Detailed Inspections (g) Perform a detailed inspection for cracking in the forward lug of the support rib 5 fitting of the left- and right-hand MLG at the time specified in paragraph (g)(1) or (g)(2) of this AD, as applicable, and repair any cracking before further flight, according to a method approved by either the Manager, International Branch, ANM–116; or the DGAC (or its delegated agent). Accomplishing the actions specified in the Airbus A318/A319/A320/A321 Nondestructive Testing Manual, Chapter 51–90– 00, revision dated February 2003, is one approved method for performing the detailed inspection. Repeat the inspection thereafter at intervals not to exceed 750 flight cycles, 600 flight hours, or 100 days, whichever occurs earliest. (1) For Model A319 and A320 series airplanes having serial numbers 537 through 625 inclusive: Do the detailed inspection within 100 days after the effective date of this AD or at the earliest of the times specified VerDate jul<14>2003 16:54 Jun 14, 2005 Jkt 205001 in paragraphs (g)(1)(i), (g)(1)(ii), and (g)(1)(iii) of this AD, whichever is later. (i) Within 750 flight cycles after accomplishing the ultrasonic inspection. (ii) Within 600 flight hours after accomplishing the ultrasonic inspection. (iii) Within 100 days after accomplishing the ultrasonic inspection. (2) For all other airplanes: Do the detailed inspection at the earliest of the times specified in paragraphs (g)(2)(i), (g)(2)(ii), and (g)(2)(iii) of this AD. (i) Within 750 flight cycles after the effective date of this AD. (ii) Within 600 flight hours after the effective date of this AD. (iii) Within 100 days 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.’’ Optional Terminating Action (h) Modification of the lugs of the support rib 5 fitting of the left- and right-hand MLG and accomplishment of all related investigative actions and all applicable corrective actions in accordance with Airbus Service Bulletin A320–57–1118, dated September 5, 2002; or Revision 01, dated August 28, 2003; constitutes compliance with the requirements of this AD. (i) Repair of the forward lugs of the support rib 5 fitting of the left- and right-hand MLG in accordance with Airbus A319 Structural Repair Manual, Chapter 5.C., 57–26–13: Airbus A320 Structural Repair Manual, Chapter 5.D., 57–26–13; and Airbus A321 Structural Repair Manual, Chapter 5.D., all revisions dated November 1, 2004, constitutes compliance with the requirements of this AD. Alternative Methods of Compliance (AMOCs) (j) 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. Related Information (k) French airworthiness directive F–2005– 035, dated March 2, 2005, also addresses the subject of this AD. Material Incorporated by Reference (l) You must use Airbus Service Bulletin A320–57A1136, dated January 26, 2005, to perform the actions that are required by this AD, unless the AD specifies otherwise. The Director of the Federal Register approves the incorporation by reference of this document in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. To get copies of the service information, contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France. To view the AD docket, go to the PO 00000 Frm 00012 Fmt 4700 Sfmt 4700 Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street SW., room PL–401, Nassif Building, Washington, DC. To review copies of the service information, go to the National Archives and Records Administration (NARA). For information on the availability of this material at the NARA, call (202) 741– 6030, or go to http://www.archives.gov/ federal_register/code_of_federal_regulations/ ibr_locations.html. Issued in Renton, Washington, on June 6, 2005. Michael J. Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 05–11707 Filed 6–14–05; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2005–21240; Directorate Identifier 2005–NM–104–AD; Amendment 39–14130; AD 2005–12–14] RIN 2120–AA64 Airworthiness Directives; Boeing Model 767–200, –300, and –400ER Series Airplanes Equipped With DoorMounted Escape Slides Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule; request for comments. AGENCY: SUMMARY: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 767–200, –300, and –400ER series airplanes. This AD requires an inspection to determine if the door-mounted escape slide/rafts have certain part numbers. For those door-mounted escape slide/rafts having certain part numbers, this AD requires an inspection for excessive tension of the firing cable, and procedures for providing slack in the firing cable or rerouting the firing cable if necessary. This AD is prompted by reports of uncommanded inflation inside the airplane of a door-mounted escape slide/raft located in the passenger compartment. We are issuing this AD to prevent injury to maintenance personnel, passengers, and crew during otherwise normal operating conditions and to prevent interference with evacuation of the airplane during an emergency, due to uncommanded inflation of a door-mounted escape slide/raft. DATES: Effective June 30, 2005. The incorporation by reference of certain publications listed in the AD is E:\FR\FM\15JNR1.SGM 15JNR1 Federal Register / Vol. 70, No. 114 / Wednesday, June 15, 2005 / Rules and Regulations approved by the Director of the Federal Register as of June 30, 2005. We must receive comments on this AD by August 15, 2005. ADDRESSES: Use one of the following addresses to submit comments on this 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. For service information identified in this AD, contact Boeing Commercial Airplanes, PO Box 3707, Seattle, Washington 98124–2207; or Goodrich Aircraft Interior Products, 3414 South 5th Street, Phoenix, Arizona 85040, as applicable. You can examine the contents of this AD docket on the Internet at http:// dms.dot.gov, or in person at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street SW., room PL–401, on the plaza level of the Nassif Building, Washington, DC. This docket number is FAA–2005– 21240; the directorate identifier for this docket is 2005–NM–104–AD. Examining the Dockets You can 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 (DMS) receives them. FOR FURTHER INFORMATION CONTACT: Susan Rosanske, Aerospace Engineer, Cabin Safety and Environmental Systems Branch, ANM–150S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98055–4056; telephone (425) 917–6448; fax (425) 917–6590. SUPPLEMENTARY INFORMATION: We have received a report indicating that three VerDate jul<14>2003 16:54 Jun 14, 2005 Jkt 205001 cases of uncommanded inflation of door-mounted escape slide/rafts occurred on Boeing Model 767–300 series airplanes. In one case, the uncommanded inflation of the doormounted escape slide/raft resulted in injury to a member of the cabin crew. In the other two incidents, damage occurred to the lavatory, ceiling panels, door bustles, and the sidewalls. Inspections by the airplane manufacturer and the escape slide/raft supplier of the factory packs and overhauled packs revealed variability in the slack/tension condition of the firing cable of the slide/rafts. The slide/rafts are designed with slack in the firing cable. Investigation revealed that a ‘‘tight’’ (excessive tension) firing cable, in combination with changes that occur in the pack as the result of the in-service environment, could result in the tension on the firing cable increasing and activating the regulator valve. This condition, if not corrected, could result in injury to maintenance personnel, passengers, and crew during otherwise normal operating conditions and could result in interference with evacuation of the airplane during an emergency, due to uncommanded inflation inside the airplane of a door-mounted escape slide/raft. Relevant Service Information We have reviewed Boeing Alert Service Bulletin (ASB) 767–25A0390, dated May 13, 2005. The ASB describes procedures for removing the cover (bustle) of the door-mounted escape slides/rafts, and performing a tension check to determine if there is excessive tension of the firing cable of the escape slides/rafts. Additionally, the ASB describes procedures for removing excessive tension of the firing cable by providing necessary slack in the firing cable, or removing the slide and rerouting the firing cable if necessary. The ASB also specifies that a general visual inspection or a records check may be accomplished to determine if certain Goodrich door-mounted escape slide/rafts are installed. The ASB refers to Goodrich Alert Service Bulletin 5A3294/5A3295– 25A356, dated May 11, 2005, as an additional source of service information. Goodrich has also issued the following packing instructions for the slide/rafts: Goodrich Packing Instructions, Evacuation Slide/Raft, Document 501636, Revision G, dated May 16, 2005; Goodrich Packing Instructions, Evacuation Slide/Raft, LH, Document 501637, Revision E, dated May 16, 2005; and Goodrich Packing Instructions, Evacuation Slide/Raft, RH, PO 00000 Frm 00013 Fmt 4700 Sfmt 4700 34639 Document 501638, Revision D, dated May 16, 2005. FAA’s Determination and Requirements of This AD The unsafe condition described previously is likely to exist or develop on other airplanes of the same type design. Therefore, we are issuing this AD to prevent injury to maintenance personnel, passengers, and crew during otherwise normal operating conditions and to prevent interference with evacuation of the airplane during an emergency, due to uncommanded inflation of a door-mounted escape slide/raft. This AD requires accomplishing the actions specified in the service information described previously. Interim Action This is considered to be interim action. The manufacturer has advised that it currently is developing a modification that will address the unsafe condition addressed by this AD. Once this modification is developed, approved, and available, we may consider additional rulemaking. FAA’s Determination of the Effective Date An unsafe condition exists that requires the immediate adoption of this AD; therefore, providing notice and opportunity for public comment before the AD is issued is impracticable, and good cause exists to make this AD effective in less than 30 days. Comments Invited This AD is a final rule that involves requirements that affect flight safety and was not preceded by notice and an opportunity for public comment; however, we invite you to submit any relevant written data, views, or arguments regarding this AD. Send your comments to an address listed under ADDRESSES. Include ‘‘Docket No. FAA– 2005–21240; Directorate Identifier 2005–NM–104–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the AD. We will consider all comments received by the closing date and may amend the 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 AD. Using the search function of our docket web site, anyone can find and read the comments E:\FR\FM\15JNR1.SGM 15JNR1 34640 Federal Register / Vol. 70, No. 114 / Wednesday, June 15, 2005 / Rules and Regulations 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 can review the DOT’s complete Privacy Act Statement in the Federal Register published on April 11, 2000 (65 FR 19477–78), or you can visit http://dms.dot.gov. 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 the 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 AD. 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. VerDate jul<14>2003 16:54 Jun 14, 2005 Jkt 205001 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 FAA amends § 39.13 by adding the following new airworthiness directive (AD): I 2005–12–14 Boeing: Amendment 39–14130. Docket No. FAA–2005–21240; Directorate Identifier 2005–NM–104–AD. Effective Date (a) This AD becomes effective June 30, 2005. Affected ADs (b) None. Applicability (c) This AD applies to Boeing Model 767– 200, –300, and –400ER series airplanes; certificated in any category; equipped with door-mounted escape slide/rafts. Unsafe Condition (d) This AD was prompted by reports of uncommanded inflation inside the airplane of a door-mounted escape slide/raft located in the passenger compartment. The FAA is issuing this AD to prevent injury to maintenance personnel, passengers, and crew during otherwise normal operating conditions and to prevent interference with evacuation of the airplane during an emergency, due to uncommanded inflation of the airplane of a door-mounted escape slide/ raft. 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. Inspection for Part Numbers (P/Ns) (f) Within 30 days after the effective date of this AD, accomplish the actions in either paragraph (f)(1) or (f)(2) of this AD. (1) Perform a one-time inspection to determine if any Goodrich door-mounted escape slide/raft having P/N 5A3294–1, 5A3294–2, 5A3295–1, or 5A3295–3 is installed. If no slide/raft having any of those P/Ns is installed, no further action is required by this paragraph, except for the requirements of paragraph (j) of this AD. (2) Perform a one-time check of the airplane maintenance records to determine if any Goodrich door-mounted escape slide/raft having P/N 5A3294–1, 5A3294–2, 5A3295–1, or 5A3295–3 is installed. If it can be conclusively determined from the airplane maintenance records that no slide/raft having any of those P/Ns is installed, no further PO 00000 Frm 00014 Fmt 4700 Sfmt 4700 action is required by this AD, except for the requirements of paragraph (j) of this AD. Inspection for Excessive Tension on the Firing Cable (g) If any door-mounted escape slide/raft with any P/N specified in paragraph (f) of this AD is installed: Within 30 days after the effective date of this AD, perform a tension check on the firing cable of the slide/raft, in accordance with Boeing Alert Service Bulletin (ASB) 767–25A0390, dated May 13, 2005. If no excessive tension is detected, no further action is required by this AD, except for the requirements of paragraph (j) of this AD. Note 1: Boeing ASB 767–25A0390, dated May 13, 2005, references Goodrich ASB 5A3294/5A3295–25A356, dated May 11, 2005, as an additional source of service information. Corrective Action for Excessive Tension on the Firing Cable (h) If any excessive tension of the firing cable is detected, before further flight, do the applicable corrective actions; in accordance with the Boeing ASB 767–25A0390, dated May 13, 2005. Previous Accomplishment (i) Inspections of the firing cables for excessive tension in accordance with Boeing ASB 767–25A0390, dated May 13, 2005, that were accomplished before the effective date of this AD are acceptable for compliance with the requirements of paragraph (g) of this AD, provided that any applicable corrective was completed. Parts Installation (j) As of the effective date of this AD, no person may install on any airplane any Goodrich door-mounted escape slide/raft having P/N 5A3294–1, 5A3294–2, 5A3295–1, or 5A3295–3, unless the tension of the firing cable has been checked and the applicable corrective action completed in accordance with Boeing ASB 767–25A0390, dated May 13, 2005, or the escape slide/raft has been repacked in accordance with Goodrich Packing Instructions, Evacuation Slide/Raft, Document 501636, Revision G, dated May 16, 2005; Goodrich Packing Instructions, Evacuation Slide/Raft, LH, Document 501637, Revision E, dated May 16, 2005; or Goodrich Packing Instructions, Evacuation Slide/Raft, RH, Document 501638, Revision D, dated May 16, 2005; as applicable. Alternative Methods of Compliance (AMOCs) (k) The Manager, Seattle Aircraft Certification Office (ACO), FAA, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19. Material Incorporated by Reference (l) You must use Boeing ASB 767– 25A0390, dated May 13, 2005, to perform the actions that are required by this AD, unless the AD specifies otherwise. The Director of the Federal Register approves the incorporation by reference of these documents in accordance with 5 U.S.C. E:\FR\FM\15JNR1.SGM 15JNR1 Federal Register / Vol. 70, No. 114 / Wednesday, June 15, 2005 / Rules and Regulations 552(a) and 1 CFR part 51. To get copies of the service information, contact Boeing Commercial Airplanes, PO Box 3707, Seattle, Washington 98124–2207; or Goodrich Aircraft Interior Products, 3414 South 5th Street, Phoenix, Arizona 85040, as applicable. To view the AD docket, go to the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street SW., room PL–401, Nassif Building, Washington, DC. To review copies of the service information, go to the National Archives and Records Administration (NARA). For information on the availability of this material at the NARA, call (202) 741– 6030, or go to http://www.archives.gov/ federal_register/code_of_federal_regulations/ ibr_locations.html. Issued in Renton, Washington, on June 7, 2005. Michael J. Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 05–11696 Filed 6–14–05; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2005–20860; Directorate Identifier 2005–NM–043–AD; Amendment 39–14131; AD 2005–12–15] RIN 2120–AA64 Airworthiness Directives; Bombardier Model DHC–8–400 Series Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: SUMMARY: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier Model DHC–8–400 series airplanes. This AD requires revising the Airworthiness Limitation section of the Instructions for Continued Airworthiness of the Dash 8 400 Series (Bombardier) Maintenance Requirements Manual to reduce the life limits of the main landing gear (MLG) orifice support tube, upper bearing, and piston plug; and to reduce the threshold for initiating repetitive detailed inspections for cracking of the engine isolator brackets. This AD is prompted by the discovery of fatigue failures, during type certification fatigue testing, at the engine isolator bracket and at the orifice support tube, upper bearing, and piston plug in the shock strut assembly of the MLG, which are principal structural elements. We are issuing this AD to prevent the development of cracks in these principal structural elements, which could reduce the VerDate jul<14>2003 16:54 Jun 14, 2005 Jkt 205001 structural integrity of the engine installation and the MLG. Reduced structural integrity of the engine installation could result in separation of the engine from the airplane, and reduced structural integrity of the MLG could result in collapse of the MLG. DATES: This AD becomes effective July 20, 2005. The incorporation by reference of certain publications listed in the AD is approved by the Director of the Federal Register as of July 20, 2005. ADDRESSES: For service information identified in this AD, contact Bombardier, Inc., Bombardier Regional Aircraft Division, 123 Garratt Boulevard, Downsview, Ontario M3K 1Y5, Canada. Docket: The AD docket contains the proposed AD, comments, and any final disposition. You can 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 U.S. Department of Transportation, 400 Seventh Street SW., room PL–401, Washington, DC. This docket number is FAA–2005–20860; the directorate identifier for this docket is 2005–NM– 043–AD. FOR FURTHER INFORMATION CONTACT: George Duckett, Aerospace Engineer, Airframe and Propulsion Branch, ANE– 171, FAA, New York Aircraft Certification Office, 1600 Stewart Avenue, Suite 410, Westbury, New York 11590; telephone (516) 228–7325; fax (516) 794–5531. SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR part 39 with an AD for certain Bombardier Model DHC–8–400 series airplanes. That action, published in the Federal Register on April 6, 2005 (70 FR 17354), proposed to require revising the Airworthiness Limitation section of the Instructions for Continued Airworthiness of the Dash 8 400 Series (Bombardier) Maintenance Requirements Manual to reduce the life limits of the main landing gear (MLG) orifice support tube, upper bearing, and piston plug; and to reduce the threshold for initiating repetitive detailed inspections for cracking of the engine isolator brackets. Explanation of Change to Applicability We have revised the applicability of the proposed AD to identify model designations as published in the most recent type certificate data sheet for the affected models. PO 00000 Frm 00015 Fmt 4700 Sfmt 4700 34641 Comments We provided the public the opportunity to participate in the development of this AD. No comments have been submitted on the proposed AD or on the determination of the cost to the public. Conclusion We have carefully reviewed the available data and determined that air safety and the public interest require adopting the AD with the change described previously. We have determined that this change will neither increase the economic burden on any operator nor increase the scope of the AD. Costs of Compliance There are about 93 airplanes of the affected design in the worldwide fleet. This AD will affect about 21 airplanes of U.S. registry. The actions will take about 1 work hour per airplane, at an average labor rate of $65 per work hour. Based on these figures, the estimated cost of the AD for U.S. operators is $1,365, or $65 per airplane. 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; E:\FR\FM\15JNR1.SGM 15JNR1

Agencies

[Federal Register Volume 70, Number 114 (Wednesday, June 15, 2005)]
[Rules and Regulations]
[Pages 34638-34641]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-11696]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-21240; Directorate Identifier 2005-NM-104-AD; 
Amendment 39-14130; AD 2005-12-14]
RIN 2120-AA64


Airworthiness Directives; Boeing Model 767-200, -300, and -400ER 
Series Airplanes Equipped With Door-Mounted Escape Slides

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

ACTION: Final rule; request for comments.

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

SUMMARY: The FAA is adopting a new airworthiness directive (AD) for 
certain Boeing Model 767-200, -300, and -400ER series airplanes. This 
AD requires an inspection to determine if the door-mounted escape 
slide/rafts have certain part numbers. For those door-mounted escape 
slide/rafts having certain part numbers, this AD requires an inspection 
for excessive tension of the firing cable, and procedures for providing 
slack in the firing cable or rerouting the firing cable if necessary. 
This AD is prompted by reports of uncommanded inflation inside the 
airplane of a door-mounted escape slide/raft located in the passenger 
compartment. We are issuing this AD to prevent injury to maintenance 
personnel, passengers, and crew during otherwise normal operating 
conditions and to prevent interference with evacuation of the airplane 
during an emergency, due to uncommanded inflation of a door-mounted 
escape slide/raft.

DATES: Effective June 30, 2005.
    The incorporation by reference of certain publications listed in 
the AD is

[[Page 34639]]

approved by the Director of the Federal Register as of June 30, 2005.
    We must receive comments on this AD by August 15, 2005.

ADDRESSES: Use one of the following addresses to submit comments on 
this 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.
    For service information identified in this AD, contact Boeing 
Commercial Airplanes, PO Box 3707, Seattle, Washington 98124-2207; or 
Goodrich Aircraft Interior Products, 3414 South 5th Street, Phoenix, 
Arizona 85040, as applicable.
    You can examine the contents of this AD docket on the Internet at 
http://dms.dot.gov, or in person at the Docket Management Facility, 
U.S. Department of Transportation, 400 Seventh Street SW., room PL-401, 
on the plaza level of the Nassif Building, Washington, DC. This docket 
number is FAA-2005-21240; the directorate identifier for this docket is 
2005-NM-104-AD.

Examining the Dockets

    You can 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 
(DMS) receives them.

FOR FURTHER INFORMATION CONTACT: Susan Rosanske, Aerospace Engineer, 
Cabin Safety and Environmental Systems Branch, ANM-150S, FAA, Seattle 
Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, 
Washington 98055-4056; telephone (425) 917-6448; fax (425) 917-6590.

SUPPLEMENTARY INFORMATION: We have received a report indicating that 
three cases of uncommanded inflation of door-mounted escape slide/rafts 
occurred on Boeing Model 767-300 series airplanes. In one case, the 
uncommanded inflation of the door-mounted escape slide/raft resulted in 
injury to a member of the cabin crew. In the other two incidents, 
damage occurred to the lavatory, ceiling panels, door bustles, and the 
sidewalls. Inspections by the airplane manufacturer and the escape 
slide/raft supplier of the factory packs and overhauled packs revealed 
variability in the slack/tension condition of the firing cable of the 
slide/rafts. The slide/rafts are designed with slack in the firing 
cable. Investigation revealed that a ``tight'' (excessive tension) 
firing cable, in combination with changes that occur in the pack as the 
result of the in-service environment, could result in the tension on 
the firing cable increasing and activating the regulator valve. This 
condition, if not corrected, could result in injury to maintenance 
personnel, passengers, and crew during otherwise normal operating 
conditions and could result in interference with evacuation of the 
airplane during an emergency, due to uncommanded inflation inside the 
airplane of a door-mounted escape slide/raft.

Relevant Service Information

    We have reviewed Boeing Alert Service Bulletin (ASB) 767-25A0390, 
dated May 13, 2005. The ASB describes procedures for removing the cover 
(bustle) of the door-mounted escape slides/rafts, and performing a 
tension check to determine if there is excessive tension of the firing 
cable of the escape slides/rafts. Additionally, the ASB describes 
procedures for removing excessive tension of the firing cable by 
providing necessary slack in the firing cable, or removing the slide 
and rerouting the firing cable if necessary. The ASB also specifies 
that a general visual inspection or a records check may be accomplished 
to determine if certain Goodrich door-mounted escape slide/rafts are 
installed.
    The ASB refers to Goodrich Alert Service Bulletin 5A3294/5A3295-
25A356, dated May 11, 2005, as an additional source of service 
information.
    Goodrich has also issued the following packing instructions for the 
slide/rafts: Goodrich Packing Instructions, Evacuation Slide/Raft, 
Document 501636, Revision G, dated May 16, 2005; Goodrich Packing 
Instructions, Evacuation Slide/Raft, LH, Document 501637, Revision E, 
dated May 16, 2005; and Goodrich Packing Instructions, Evacuation 
Slide/Raft, RH, Document 501638, Revision D, dated May 16, 2005.

FAA's Determination and Requirements of This AD

    The unsafe condition described previously is likely to exist or 
develop on other airplanes of the same type design. Therefore, we are 
issuing this AD to prevent injury to maintenance personnel, passengers, 
and crew during otherwise normal operating conditions and to prevent 
interference with evacuation of the airplane during an emergency, due 
to uncommanded inflation of a door-mounted escape slide/raft. This AD 
requires accomplishing the actions specified in the service information 
described previously.

Interim Action

    This is considered to be interim action. The manufacturer has 
advised that it currently is developing a modification that will 
address the unsafe condition addressed by this AD. Once this 
modification is developed, approved, and available, we may consider 
additional rulemaking.

FAA's Determination of the Effective Date

    An unsafe condition exists that requires the immediate adoption of 
this AD; therefore, providing notice and opportunity for public comment 
before the AD is issued is impracticable, and good cause exists to make 
this AD effective in less than 30 days.

Comments Invited

    This AD is a final rule that involves requirements that affect 
flight safety and was not preceded by notice and an opportunity for 
public comment; however, we invite you to submit any relevant written 
data, views, or arguments regarding this AD. Send your comments to an 
address listed under ADDRESSES. Include ``Docket No. FAA-2005-21240; 
Directorate Identifier 2005-NM-104-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of the AD. We will consider 
all comments received by the closing date and may amend the 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 AD. Using the search function of our docket 
web site, anyone can find and read the comments

[[Page 34640]]

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 can review the DOT's complete Privacy 
Act Statement in the Federal Register published on April 11, 2000 (65 
FR 19477-78), or you can visit http://dms.dot.gov.

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 the 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 AD. See the ADDRESSES section for a location to 
examine the regulatory evaluation.

List of Subjects in 14 CFR Part 39

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

Adoption of the Amendment

0
Accordingly, under the authority delegated to me by the Administrator, 
the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

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

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


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive (AD):

2005-12-14 Boeing: Amendment 39-14130. Docket No. FAA-2005-21240; 
Directorate Identifier 2005-NM-104-AD.

Effective Date

    (a) This AD becomes effective June 30, 2005.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Boeing Model 767-200, -300, and -400ER 
series airplanes; certificated in any category; equipped with door-
mounted escape slide/rafts.

Unsafe Condition

    (d) This AD was prompted by reports of uncommanded inflation 
inside the airplane of a door-mounted escape slide/raft located in 
the passenger compartment. The FAA is issuing this AD to prevent 
injury to maintenance personnel, passengers, and crew during 
otherwise normal operating conditions and to prevent interference 
with evacuation of the airplane during an emergency, due to 
uncommanded inflation of the airplane of a door-mounted escape 
slide/raft.

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.

Inspection for Part Numbers (P/Ns)

    (f) Within 30 days after the effective date of this AD, 
accomplish the actions in either paragraph (f)(1) or (f)(2) of this 
AD.
    (1) Perform a one-time inspection to determine if any Goodrich 
door-mounted escape slide/raft having P/N 5A3294-1, 5A3294-2, 
5A3295-1, or 5A3295-3 is installed. If no slide/raft having any of 
those P/Ns is installed, no further action is required by this 
paragraph, except for the requirements of paragraph (j) of this AD.
    (2) Perform a one-time check of the airplane maintenance records 
to determine if any Goodrich door-mounted escape slide/raft having 
P/N 5A3294-1, 5A3294-2, 5A3295-1, or 5A3295-3 is installed. If it 
can be conclusively determined from the airplane maintenance records 
that no slide/raft having any of those P/Ns is installed, no further 
action is required by this AD, except for the requirements of 
paragraph (j) of this AD.

Inspection for Excessive Tension on the Firing Cable

    (g) If any door-mounted escape slide/raft with any P/N specified 
in paragraph (f) of this AD is installed: Within 30 days after the 
effective date of this AD, perform a tension check on the firing 
cable of the slide/raft, in accordance with Boeing Alert Service 
Bulletin (ASB) 767-25A0390, dated May 13, 2005. If no excessive 
tension is detected, no further action is required by this AD, 
except for the requirements of paragraph (j) of this AD.

    Note 1: Boeing ASB 767-25A0390, dated May 13, 2005, references 
Goodrich ASB 5A3294/5A3295-25A356, dated May 11, 2005, as an 
additional source of service information.

Corrective Action for Excessive Tension on the Firing Cable

    (h) If any excessive tension of the firing cable is detected, 
before further flight, do the applicable corrective actions; in 
accordance with the Boeing ASB 767-25A0390, dated May 13, 2005.

Previous Accomplishment

    (i) Inspections of the firing cables for excessive tension in 
accordance with Boeing ASB 767-25A0390, dated May 13, 2005, that 
were accomplished before the effective date of this AD are 
acceptable for compliance with the requirements of paragraph (g) of 
this AD, provided that any applicable corrective was completed.

Parts Installation

    (j) As of the effective date of this AD, no person may install 
on any airplane any Goodrich door-mounted escape slide/raft having 
P/N 5A3294-1, 5A3294-2, 5A3295-1, or 5A3295-3, unless the tension of 
the firing cable has been checked and the applicable corrective 
action completed in accordance with Boeing ASB 767-25A0390, dated 
May 13, 2005, or the escape slide/raft has been repacked in 
accordance with Goodrich Packing Instructions, Evacuation Slide/
Raft, Document 501636, Revision G, dated May 16, 2005; Goodrich 
Packing Instructions, Evacuation Slide/Raft, LH, Document 501637, 
Revision E, dated May 16, 2005; or Goodrich Packing Instructions, 
Evacuation Slide/Raft, RH, Document 501638, Revision D, dated May 
16, 2005; as applicable.

Alternative Methods of Compliance (AMOCs)

    (k) The Manager, Seattle Aircraft Certification Office (ACO), 
FAA, has the authority to approve AMOCs for this AD, if requested in 
accordance with the procedures found in 14 CFR 39.19.

Material Incorporated by Reference

    (l) You must use Boeing ASB 767-25A0390, dated May 13, 2005, to 
perform the actions that are required by this AD, unless the AD 
specifies otherwise. The Director of the Federal Register approves 
the incorporation by reference of these documents in accordance with 
5 U.S.C.

[[Page 34641]]

552(a) and 1 CFR part 51. To get copies of the service information, 
contact Boeing Commercial Airplanes, PO Box 3707, Seattle, 
Washington 98124-2207; or Goodrich Aircraft Interior Products, 3414 
South 5th Street, Phoenix, Arizona 85040, as applicable. To view the 
AD docket, go to the Docket Management Facility, U.S. Department of 
Transportation, 400 Seventh Street SW., room PL-401, Nassif 
Building, Washington, DC. To review copies of the service 
information, go to the National Archives and Records Administration 
(NARA). For information on the availability of this material at the 
NARA, call (202) 741-6030, or go to http://www.archives.gov/
federal_register/code_of_federal_regulations/ibr_
locations.html.

    Issued in Renton, Washington, on June 7, 2005.
Michael J. Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 05-11696 Filed 6-14-05; 8:45 am]
BILLING CODE 4910-13-P