Federal Register / Vol. 70, No. 119 / Wednesday, June 22, 2005 / Rules and Regulations 35989

2005–13–02 Bombardier, Inc. (Formerly Affected ADs Summary 670T11508 or Bombardier Service Canadair): Amendment 39–14138. (b) None. Bulletin 670BA–29–008, dated March 12, Docket No. FAA–2004–19754; Applicability: (c) This AD applies to the 2004, or Revision A, dated May 5, 2004; has Directorate Identifier 2004–NM–181–AD. airplanes listed in Table 1 of this AD, been incorporated in production. Effective Date certificated in any category, excluding those (a) This AD becomes effective July 27, airplanes on which Modification Summaries 2005. 670T00494 or 670T11944; and Modification

TABLE 1.—APPLICABILITY

Bombardier model Serial numbers

(1) CL–600–2C10 ( Series 700 & 701) series airplanes ...... 10003 through 10999 inclusive. (2) CL–600–2D24 (Regional Jet Series 900) series airplanes ...... 15001 through 15990 inclusive.

Unsafe Condition (1) Before further flight, repair the crack in Bombardier, Inc., Canadair, Aerospace (d) This AD was prompted by reports of accordance with a method approved by Group, P.O. Box 6087, Station Centre-ville, hydraulic pressure loss in either the number either the Manager, New York Aircraft , H3C 3G9, . To view 1 or number 2 hydraulic system due to Certification Office (ACO), FAA; or Transport the AD docket, contact the Docket breakage or leakage of hydraulic lines in the Canada Civil Aviation (TCCA) (or its Management Facility, U.S. Department of aft equipment bay and reports of cracks on delegated agent). Transportation, 400 Seventh Street SW., the aft pressure bulkhead web around these (2) At the applicable time specified in room PL–401, Nassif Building, Washington, feed-through holes. We are issuing this AD to paragraph (h)(2)(i) or (h)(2)(ii) of this AD, DC. To review copies of the service prevent loss of hydraulic pressure, which revise the Airworthiness Limitations section information, go to the National Archives and could result in reduced controllability of the of the Instructions of Continued Records Administration (NARA). For airplane, and to detect and correct cracks on Airworthiness by inserting a copy of the information on the availability of this the aft pressure bulkhead web, which could inspection requirements for the repair material at the NARA, call (202) 741–6030, result in reduced structural integrity of the required by paragraph (h)(1) of this AD into or go to http://www.archives.gov/ aft pressure bulkhead. Section 1.4, Part 2 (Airworthiness federal_register/code_of_federal Compliance: (e) You are responsible for Limitations), of Bombardier Regional Jet _regulations/ibr_locations.html. having the actions required by this AD Model CL–600–2C10 and CL–600–2D24 Maintenance Requirements Manual, CSP B– Issued in Renton, Washington, on June 10, performed within the compliance times 2005. specified, unless the actions have already 053. Thereafter, except as provided in been done. paragraph (i) of this AD, no alternative Michael Kaszycki, structural inspection intervals may be Acting Manager, Transport Airplane Revision of Airworthiness Limitations approved for this aft pressure bulkhead and Directorate, Aircraft Certification Service. Section pylon pressure pan in the vicinity of the [FR Doc. 05–12000 Filed 6–21–05; 8:45 am] hydraulic fittings, and the hydraulic tube (f) Within 30 days after the effective date BILLING CODE 4910–13–P of this AD, revise the Airworthiness adapters. Limitations section of the Instructions of (i) If the repair required by paragraph (h)(1) Continued Airworthiness by inserting a copy of this AD is done after the effective date of of the new repetitive inspections and an this AD: Revise the Airworthiness DEPARTMENT OF TRANSPORTATION optional terminating action of Bombardier Limitations section within 12 months after CRJ 700/900 Series Temporary Revision (TR) the repair. Federal Aviation Administration MRM2–129, dated June 1, 2004, into Section (ii) If the repair required by paragraph 1.4, Part 2 (Airworthiness Limitations), of (h)(1) of this AD was accomplished before the 14 CFR Part 39 effective date of this AD: Revise the Bombardier Regional Jet Model CL–600–2C10 [Docket No. FAA–2004–19678; Directorate and CL–600–2D24 Maintenance Airworthiness Limitations section within 12 Identifier 2004–NM–62–AD; Amendment 39– Requirements Manual, CSP B–053. months after the repair or 30 days after the 14141; AD 2005–13–05] Thereafter, except as provided in paragraph effective date of this AD, whichever occurs (h)(2) or (i) of this AD, no alternative later. RIN 2120–AA64 structural inspection intervals may be Alternative Methods of Compliance approved for this aft pressure bulkhead and (AMOCs) Airworthiness Directives; Boeing pylon pressure pan in the vicinity of the Model 747–400F Series Airplanes hydraulic fittings and the hydraulic tube (i) The Manager, New York ACO, FAA, has adapters. the authority to approve AMOCs for this AD, AGENCY: Federal Aviation (g) When the information in TR MRM2– if requested in accordance with the Administration (FAA), Department of 129, dated June 1, 2004, is included in the procedures found in 14 CFR 39.19. Transportation (DOT). general revisions of the Maintenance Related Information Requirement Manual, the general revisions ACTION: Final rule. may be inserted into the Airworthiness (j) Canadian airworthiness directive CF– SUMMARY: Limitations section of the Instructions of 2004–14, dated July 20, 2004, also addresses The FAA is adopting a new Continued Airworthiness and this TR may be the subject of this AD. airworthiness directive (AD) for certain removed. Boeing Model 747–400F series Material Incorporated by Reference airplanes. This AD requires initial Corrective Action (k) You must use Bombardier CRJ 700/900 detailed and open-hole high frequency (h) If any crack is found during any Series Temporary Revision MRM2–129, eddy current inspections for cracking of inspection done in accordance with dated June 1, 2004, to perform the actions the web, upper chord, and upper chord that are required by this AD, unless the AD Bombardier CRJ 700/900 Series TR MRM2– strap of the upper deck floor beams, and 129, dated June 1, 2004, or the same specifies otherwise. The Director of the inspection specified in the general revisions Federal Register approves the incorporation repair of any cracking. This AD also of the Maintenance Requirement Manual, do by reference of this document in accordance requires a preventive modification of the actions specified in paragraphs (h)(1) and with 5 U.S.C. 552(a) and 1 CFR part 51. To the upper deck floor beams, and (h)(2) of this AD. get copies of the service information, contact repetitive inspections for cracking after

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accomplishing the modification. This disposition. You can examine the AD inspections for cracking of the web, AD is prompted by reports of fatigue docket on the Internet at http:// upper chord, and upper chord strap of cracking found on the upper deck floor dms.dot.gov, or in person at the Docket the upper deck floor beams, and repair beam to frame attachment points. We Management Facility office between 9 of any cracking. That action also are issuing this AD to prevent fatigue a.m. and 5 p.m., Monday through proposed to require a preventive cracks in the upper chord, upper chord Friday, except Federal holidays. The modification of the upper deck floor strap, and the web of the upper deck Docket Management Facility office beams, and repetitive inspections for floor beams and resultant failure of the (telephone (800) 647–5227) is located on cracking after accomplishing the floor beams. Failure of a floor beam the plaza level of the Nassif Building at modification. could result in damage to critical flight the U.S. Department of Transportation, Comments control cables and wire bundles that 400 Seventh Street SW., room PL–401, pass through the floor beam, and Washington, DC. This docket number is We provided the public the consequent loss of controllability of the FAA–2004–19678; the directorate opportunity to participate in the airplane. Failure of the floor beam also identifier for this docket is 2004–NM– development of this AD. No comments could result in the failure of the 62–AD. have been submitted on the proposed AD or on the determination of the cost adjacent fuselage frames and skin, and FOR FURTHER INFORMATION CONTACT: Ivan to the public. consequent rapid decompression of the Li, Aerospace Engineer, Airframe airplane. Branch, ANM–120S, FAA, Seattle Conclusion DATES: This AD becomes effective July Aircraft Certification Office, 1601 Lind We have carefully reviewed the 27, 2005. Avenue, SW., Renton, Washington available data and determined that air The incorporation by reference of a 98055–4056; telephone (425) 917–6437; safety and the public interest require certain publication listed in the AD is fax (425) 917–6590. adopting the AD as proposed. approved by the Director of the Federal SUPPLEMENTARY INFORMATION: The FAA Register as of July 27, 2005. proposed to amend 14 CFR part 39 with Costs of Compliance ADDRESSES: For service information an AD for certain Boeing Model 747– This AD affects about 53 airplanes identified in this AD, contact Boeing 400F series airplanes. That action, worldwide and 13 airplanes of U.S. Commercial Airplanes, P.O. Box 3707, published in the Federal Register on registry. The following table provides Seattle, Washington 98124–2207. November 24, 2004 (69 FR 68277), the estimated costs for U.S. operators to Docket: The AD docket contains the proposed to require initial detailed and comply with this AD, depending on the proposed AD, comments, and any final open-hole high frequency eddy current airplane configuration:

ESTIMATED COSTS

Number of af- Average Cost per fected U.S.- Action Work hours labor rate Parts airplane registered Fleet cost per hour airplanes

Pre-modification inspections ...... 11 ...... $65 $0 ...... $715 ...... 13 $9,295 Modification/Inspections done during modification .... 498 or 524 ... 65 $13,554 or $45,924 or 13 $597,012 or $14,874. $48,934. $636,142 Post-modification inspections ...... 66 ...... 65 $0 ...... $4,290, per 13 $55,770 inspection cycle.

Authority for This Rulemaking products identified in this rulemaking under the criteria of the Regulatory action. Flexibility Act. Title 49 of the United States Code specifies the FAA’s authority to issue Regulatory Findings We prepared a regulatory evaluation of the estimated costs to comply with rules on aviation safety. Subtitle I, We have determined that this AD will this AD. See the ADDRESSES section 106, describes the authority of not have federalism implications under section for the FAA Administrator. Subtitle VII, Executive Order 13132. This AD will a location to examine the regulatory Aviation Programs, describes in more not have a substantial direct effect on evaluation. detail the scope of the Agency’s the States, on the relationship between List of Subjects in 14 CFR Part 39 authority. the national government and the States, We are issuing this rulemaking under or on the distribution of power and Air transportation, Aircraft, Aviation the authority described in subtitle VII, responsibilities among the various safety, Incorporation by reference, part A, subpart III, section 44701, levels of government. Safety. ‘‘General requirements.’’ Under that For the reasons discussed above, I section, Congress charges the FAA with certify that this AD: Adoption of the Amendment promoting safe flight of civil aircraft in (1) Is not a ‘‘significant regulatory I Accordingly, under the authority air commerce by prescribing regulations action’’ under Executive Order 12866; for practices, methods, and procedures (2) Is not a ‘‘significant rule’’ under delegated to me by the Administrator, the Administrator finds necessary for DOT Regulatory Policies and Procedures the FAA amends 14 CFR part 39 as safety in air commerce. This regulation (44 FR 11034, February 26, 1979); and follows: is within the scope of that authority (3) Will not have a significant because it addresses an unsafe condition economic impact, positive or negative, that is likely to exist or develop on on a substantial number of small entities

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PART 39—AIRWORTHINESS cleaning and elaborate procedures may be the inspections at intervals not to exceed DIRECTIVES required.’’ 1,000 flight cycles. (2) Accomplish detailed and open-hole I (h) If any crack is found during any 1. The authority citation for part 39 inspection required by paragraph (g) of this HFEC inspections for cracking of the web, continues to read as follows: AD: Before further flight, accomplish the upper chord, and strap of the upper deck Authority: 49 U.S.C. 106(g), 40113, 44701. actions required by paragraph (h)(1) and floor beams, by doing all the applicable (h)(2) of this AD. actions in accordance with Part 3.B.5. of the § 39.13 [Amended] (1) Repair in accordance with the service service bulletin. If no crack is found, repeat I 2. The FAA amends § 39.13 by adding bulletin; except where the service bulletin the inspections at intervals not to exceed specifies to contact Boeing for appropriate 5,000 flight cycles. the following new airworthiness action, before further flight, repair in directive (AD): accordance with a method approved by the Note 2: There is no terminating action 2005–13–05 Boeing: Amendment 39–14141. Manager, Seattle Aircraft Certification Office currently available for the repetitive Docket No. FAA–2004–19678; (ACO), FAA; or according to data meeting the inspections required by this AD. Directorate Identifier 2004–NM–62–AD. type certification basis of the airplane approved by a Boeing Company Designated Alternative Methods of Compliance Effective Date Engineering Representative (DER) who has (AMOCs) (a) This AD becomes effective July 27, been authorized by the Manager, Seattle (k)(1) The Manager, Seattle ACO, has the ACO, to make such findings. For a repair 2005. authority to approve AMOCs for this AD, if method to be approved by the Manager, Affected ADs Seattle ACO, as required by this paragraph, requested in accordance with the procedures (b) None. the Manager’s approval letter must found in 14 CFR 39.19. Applicability: (c) This AD applies to Model specifically reference this AD. (2) An AMOC that provides an acceptable 747–400F series airplanes, certificated in any (2) Accomplish the inspections and level of safety may be used for any repair category, as listed in Boeing Alert Service preventive modification of the floor beams by required by this AD, if it is approved by a Bulletin 747–53A2443, dated May 9, 2002. doing all the actions in accordance with Part Boeing Company DER who has been 3.B.2. or Part 3.B.3. of the service bulletin, as Unsafe Condition authorized by the Manager, Seattle ACO, to applicable. If any crack is found during any make those findings. For a repair method to (d) This AD was prompted by reports of inspection, before further flight, repair as be approved, the approval must specifically fatigue cracking found on the upper deck required by paragraph (h)(1) of this AD. refer to this AD. floor beam to frame attachment points. We (i) If no crack is found during any are issuing this AD to prevent fatigue cracks inspection required by paragraph (g) of this Material Incorporated by Reference in the upper chord, upper chord strap, and AD: Accomplish the actions required by web of the upper deck floor beams and the either paragraph (i)(1) or (i)(2) of this AD, at (l) You must use Boeing Alert Service resultant failure of the floor beams. Failure of the time specified. Bulletin 747–53A2443, dated May 9, 2002, to a floor beam could result in damage to (1) Before further flight: Accomplish the perform the actions that are required by this critical flight control cables and wire bundles inspections and preventive modification of AD, unless the AD specifies otherwise. The that pass through the floor beam, and the floor beam by doing all the actions in Director of the Federal Register approves the consequent loss of controllability of the accordance with Part 3.B.2 or Part 3.B.3. of incorporation by reference of this document airplane. Failure of the floor beam also could the service bulletin, as applicable. If the in accordance with 5 U.S.C. 552(a) and 1 CFR result in the failure of the adjacent fuselage preventive modification is performed part 51. To get copies of the service frames and skin, and consequent rapid concurrently with the inspections required information, contact Boeing Commercial decompression of the airplane. by paragraph (g) of this AD, the upper chord Airplanes, P.O. Box 3707, Seattle, Compliance: (e) You are responsible for straps must be removed when performing the having the actions required by this AD open-hole HFEC inspection. If any crack is Washington 98124–2207. To view the AD performed within the compliance times found during any inspection, before further docket, go to the Docket Management specified, unless the actions have already flight, repair as required by paragraph (h)(1) Facility, U.S. Department of Transportation, been done. of this AD. 400 Seventh Street SW., room PL–401, Nassif Service Bulletin Reference (2) Before the accumulation of 20,000 total Building, Washington, DC. To review copies flight cycles, or within 1,000 flight cycles of the service information, go to the National (f) For the purposes of this AD, the term after the effective date of this AD, whichever Archives and Records Administration ‘‘service bulletin’’ means the is later: Accomplish the inspections and Accomplishment Instructions of Boeing Alert (NARA). For information on the availability preventive modification of the upper deck of this material at the NARA, call (202) 741– Service Bulletin 747–53A2443, dated May 9, floor beams, by doing all the actions in 6030, or go to http://www.archives.gov/ 2002. accordance with Part 3.B.2. or 3.B.3. of the federal_register/code_of_federal_regulations/ Inspections/Repair/Modification service bulletin, as applicable. If any crack is _ found during any inspection, before further ibr locations.html. (g) Before the accumulation of 15,000 total flight, repair as required by paragraph (h)(1) Issued in Renton, Washington, on June 10, flight cycles, or within 1,000 flight cycles of this AD. after the effective date of this AD, whichever 2005. is later: Accomplish detailed and open-hole Post-Modification Inspections Michael Kaszycki, high frequency eddy current (HFEC) (j) Within 15,000 flight cycles after Acting Manager, Transport Airplane inspections for cracking of the web, upper accomplishing the applicable preventive Directorate, Aircraft Certification Service. chord, and upper chord strap of the upper modification required by paragraph (h)(2), [FR Doc. 05–12002 Filed 6–21–05; 8:45 am] deck floor beams, by doing all the applicable (i)(1), or (i)(2) of this AD: Accomplish the actions in accordance with Part 3.B.1. of the inspections required by either paragraph BILLING CODE 4910–13–P service bulletin. (j)(1) or (j)(2) of this AD; if any crack is found Note 1: For the purposes of this AD, a during any inspection, before further flight, detailed inspection is: ‘‘An intensive repair as required by paragraph (h)(1) of this examination of a specific item, installation, AD. or assembly to detect damage, failure, or (1) Accomplish detailed and surface HFEC irregularity. Available lighting is normally inspections for cracking of the web, upper supplemented with a direct source of good chord, and upper chord strap of the upper lighting at an intensity deemed appropriate. deck floor beams, by doing all the applicable Inspection aids such as mirror, magnifying actions in accordance with Part 3.B.4. of the lenses, etc., may be necessary. Surface service bulletin. If no crack is found, repeat

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