Airworthiness Directives; Boeing Model 747-400F Series Airplanes, 35989-35991 [05-12002]

Download as PDF Federal Register / Vol. 70, No. 119 / Wednesday, June 22, 2005 / Rules and Regulations 2005–13–02 Bombardier, Inc. (Formerly Canadair): Amendment 39–14138. Docket No. FAA–2004–19754; Directorate Identifier 2004–NM–181–AD. Effective Date (a) This AD becomes effective July 27, 2005. Affected ADs (b) None. Applicability: (c) This AD applies to the airplanes listed in Table 1 of this AD, certificated in any category, excluding those airplanes on which Modification Summaries 670T00494 or 670T11944; and Modification 35989 Summary 670T11508 or Bombardier Service Bulletin 670BA–29–008, dated March 12, 2004, or Revision A, dated May 5, 2004; has been incorporated in production. TABLE 1.—APPLICABILITY Bombardier model Serial numbers (1) CL–600–2C10 (Regional Jet Series 700 & 701) series airplanes .................................................................. (2) CL–600–2D24 (Regional Jet Series 900) series airplanes ............................................................................. Unsafe Condition (d) This AD was prompted by reports of hydraulic pressure loss in either the number 1 or number 2 hydraulic system due to breakage or leakage of hydraulic lines in the aft equipment bay and reports of cracks on the aft pressure bulkhead web around these feed-through holes. We are issuing this AD to prevent loss of hydraulic pressure, which could result in reduced controllability of the airplane, and to detect and correct cracks on the aft pressure bulkhead web, which could result in reduced structural integrity of the aft pressure bulkhead. 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. Revision of Airworthiness Limitations Section (f) Within 30 days after the effective date of this AD, revise the Airworthiness Limitations section of the Instructions of Continued Airworthiness by inserting a copy of the new repetitive inspections and an optional terminating action of Bombardier CRJ 700/900 Series Temporary Revision (TR) MRM2–129, dated June 1, 2004, into Section 1.4, Part 2 (Airworthiness Limitations), of Bombardier Regional Jet Model CL–600–2C10 and CL–600–2D24 Maintenance Requirements Manual, CSP B–053. Thereafter, except as provided in paragraph (h)(2) or (i) of this AD, no alternative structural inspection intervals may be approved for this aft pressure bulkhead and pylon pressure pan in the vicinity of the hydraulic fittings and the hydraulic tube adapters. (g) When the information in TR MRM2– 129, dated June 1, 2004, is included in the general revisions of the Maintenance Requirement Manual, the general revisions may be inserted into the Airworthiness Limitations section of the Instructions of Continued Airworthiness and this TR may be removed. Corrective Action (h) If any crack is found during any inspection done in accordance with Bombardier CRJ 700/900 Series TR MRM2– 129, dated June 1, 2004, or the same inspection specified in the general revisions of the Maintenance Requirement Manual, do the actions specified in paragraphs (h)(1) and (h)(2) of this AD. VerDate jul<14>2003 15:52 Jun 21, 2005 Jkt 205001 (1) Before further flight, repair the crack in accordance with a method approved by either the Manager, New York Aircraft Certification Office (ACO), FAA; or Transport Canada Civil Aviation (TCCA) (or its delegated agent). (2) At the applicable time specified in paragraph (h)(2)(i) or (h)(2)(ii) of this AD, revise the Airworthiness Limitations section of the Instructions of Continued Airworthiness by inserting a copy of the inspection requirements for the repair required by paragraph (h)(1) of this AD into Section 1.4, Part 2 (Airworthiness Limitations), of Bombardier Regional Jet Model CL–600–2C10 and CL–600–2D24 Maintenance Requirements Manual, CSP B– 053. Thereafter, except as provided in paragraph (i) of this AD, no alternative structural inspection intervals may be approved for this aft pressure bulkhead and pylon pressure pan in the vicinity of the hydraulic fittings, and the hydraulic tube adapters. (i) If the repair required by paragraph (h)(1) of this AD is done after the effective date of this AD: Revise the Airworthiness Limitations section within 12 months after the repair. (ii) If the repair required by paragraph (h)(1) of this AD was accomplished before the effective date of this AD: Revise the Airworthiness Limitations section within 12 months after the repair or 30 days after the effective date of this AD, whichever occurs later. Alternative Methods of Compliance (AMOCs) (i) The Manager, New York ACO, FAA, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19. Related Information (j) Canadian airworthiness directive CF– 2004–14, dated July 20, 2004, also addresses the subject of this AD. Material Incorporated by Reference (k) You must use Bombardier CRJ 700/900 Series Temporary Revision MRM2–129, dated June 1, 2004, 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 PO 00000 Frm 00005 Fmt 4700 Sfmt 4700 10003 through 10999 inclusive. 15001 through 15990 inclusive. Bombardier, Inc., Canadair, Aerospace Group, P.O. Box 6087, Station Centre-ville, Montreal, Quebec H3C 3G9, Canada. To view the AD docket, contact 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 10, 2005. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 05–12000 Filed 6–21–05; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2004–19678; Directorate Identifier 2004–NM–62–AD; Amendment 39– 14141; AD 2005–13–05] RIN 2120–AA64 Airworthiness Directives; Boeing Model 747–400F 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 Boeing Model 747–400F series airplanes. This AD requires initial detailed and open-hole high frequency eddy current inspections for cracking of the web, upper chord, and upper chord strap of the upper deck floor beams, and repair of any cracking. This AD also requires a preventive modification of the upper deck floor beams, and repetitive inspections for cracking after E:\FR\FM\22JNR1.SGM 22JNR1 35990 Federal Register / Vol. 70, No. 119 / Wednesday, June 22, 2005 / Rules and Regulations accomplishing the modification. This AD is prompted by reports of fatigue cracking found on the upper deck floor beam to frame attachment points. We are issuing this AD to prevent fatigue cracks in the upper chord, upper chord strap, and the web of the upper deck floor beams and resultant failure of the floor beams. Failure of a floor beam could result in damage to critical flight control cables and wire bundles that pass through the floor beam, and consequent loss of controllability of the airplane. Failure of the floor beam also could result in the failure of the adjacent fuselage frames and skin, and consequent rapid decompression of the airplane. DATES: This AD becomes effective July 27, 2005. The incorporation by reference of a certain publication listed in the AD is approved by the Director of the Federal Register as of July 27, 2005. ADDRESSES: For service information identified in this AD, contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124–2207. 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–2004–19678; the directorate identifier for this docket is 2004–NM– 62–AD. Ivan Li, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98055–4056; telephone (425) 917–6437; fax (425) 917–6590. FOR FURTHER INFORMATION CONTACT: The FAA proposed to amend 14 CFR part 39 with an AD for certain Boeing Model 747– 400F series airplanes. That action, published in the Federal Register on November 24, 2004 (69 FR 68277), proposed to require initial detailed and open-hole high frequency eddy current SUPPLEMENTARY INFORMATION: inspections for cracking of the web, upper chord, and upper chord strap of the upper deck floor beams, and repair of any cracking. That action also proposed to require a preventive modification of the upper deck floor beams, and repetitive inspections for cracking after accomplishing the modification. 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 as proposed. Costs of Compliance This AD affects about 53 airplanes worldwide and 13 airplanes of U.S. registry. The following table provides the estimated costs for U.S. operators to comply with this AD, depending on the airplane configuration: ESTIMATED COSTS Average labor rate per hour Action Work hours Pre-modification inspections ...................................... Modification/Inspections done during modification .... 11 ................ 498 or 524 ... $65 65 Post-modification inspections .................................... 66 ................ 65 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 VerDate jul<14>2003 15:52 Jun 21, 2005 Jkt 205001 Parts Cost per airplane $0 ................ $13,554 or $14,874. $0 ................ $715 ............ $45,924 or $48,934. $4,290, per inspection cycle. products identified in this rulemaking action. Regulatory Findings We have determined that this AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that this AD: (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866; (2) Is not a ‘‘significant rule’’ under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and (3) Will not have a significant economic impact, positive or negative, on a substantial number of small entities PO 00000 Frm 00006 Fmt 4700 Sfmt 4700 Number of affected U.S.registered airplanes 13 13 13 Fleet cost $9,295 $597,012 or $636,142 $55,770 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 Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: I E:\FR\FM\22JNR1.SGM 22JNR1 Federal Register / Vol. 70, No. 119 / Wednesday, June 22, 2005 / Rules and Regulations PART 39—AIRWORTHINESS DIRECTIVES cleaning and elaborate procedures may be required.’’ 1. The authority citation for part 39 continues to read as follows: (h) If any crack is found during any inspection required by paragraph (g) of this AD: Before further flight, accomplish the actions required by paragraph (h)(1) and (h)(2) of this AD. (1) Repair in accordance with the service bulletin; except where the service bulletin specifies to contact Boeing for appropriate action, before further flight, repair in accordance with a method approved by the Manager, Seattle Aircraft Certification Office (ACO), FAA; or according to data meeting the type certification basis of the airplane approved by a Boeing Company Designated Engineering Representative (DER) who has been authorized by the Manager, Seattle ACO, to make such findings. For a repair method to be approved by the Manager, Seattle ACO, as required by this paragraph, the Manager’s approval letter must specifically reference this AD. (2) Accomplish the inspections and preventive modification of the floor beams by doing all the actions in accordance with Part 3.B.2. or Part 3.B.3. of the service bulletin, as applicable. If any crack is found during any inspection, before further flight, repair as required by paragraph (h)(1) of this AD. (i) If no crack is found during any inspection required by paragraph (g) of this AD: Accomplish the actions required by either paragraph (i)(1) or (i)(2) of this AD, at the time specified. (1) Before further flight: Accomplish the inspections and preventive modification of the floor beam by doing all the actions in accordance with Part 3.B.2 or Part 3.B.3. of the service bulletin, as applicable. If the preventive modification is performed concurrently with the inspections required by paragraph (g) of this AD, the upper chord straps must be removed when performing the open-hole HFEC inspection. If any crack is found during any inspection, before further flight, repair as required by paragraph (h)(1) of this AD. (2) Before the accumulation of 20,000 total flight cycles, or within 1,000 flight cycles after the effective date of this AD, whichever is later: Accomplish the inspections and preventive modification of the upper deck floor beams, by doing all the actions in accordance with Part 3.B.2. or 3.B.3. of the service bulletin, as applicable. If any crack is found during any inspection, before further flight, repair as required by paragraph (h)(1) of this AD. 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 2005–13–05 Boeing: Amendment 39–14141. Docket No. FAA–2004–19678; Directorate Identifier 2004–NM–62–AD. Effective Date (a) This AD becomes effective July 27, 2005. Affected ADs (b) None. Applicability: (c) This AD applies to Model 747–400F series airplanes, certificated in any category, as listed in Boeing Alert Service Bulletin 747–53A2443, dated May 9, 2002. Unsafe Condition (d) This AD was prompted by reports of fatigue cracking found on the upper deck floor beam to frame attachment points. We are issuing this AD to prevent fatigue cracks in the upper chord, upper chord strap, and web of the upper deck floor beams and the resultant failure of the floor beams. Failure of a floor beam could result in damage to critical flight control cables and wire bundles that pass through the floor beam, and consequent loss of controllability of the airplane. Failure of the floor beam also could result in the failure of the adjacent fuselage frames and skin, and consequent rapid decompression 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. Service Bulletin Reference (f) For the purposes of this AD, the term ‘‘service bulletin’’ means the Accomplishment Instructions of Boeing Alert Service Bulletin 747–53A2443, dated May 9, 2002. Inspections/Repair/Modification (g) Before the accumulation of 15,000 total flight cycles, or within 1,000 flight cycles after the effective date of this AD, whichever is later: Accomplish detailed and open-hole high frequency eddy current (HFEC) inspections for cracking of the web, upper chord, and upper chord strap of the upper deck floor beams, by doing all the applicable actions in accordance with Part 3.B.1. of the service bulletin. 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 VerDate jul<14>2003 15:52 Jun 21, 2005 Jkt 205001 Post-Modification Inspections (j) Within 15,000 flight cycles after accomplishing the applicable preventive modification required by paragraph (h)(2), (i)(1), or (i)(2) of this AD: Accomplish the inspections required by either paragraph (j)(1) or (j)(2) of this AD; if any crack is found during any inspection, before further flight, repair as required by paragraph (h)(1) of this AD. (1) Accomplish detailed and surface HFEC inspections for cracking of the web, upper chord, and upper chord strap of the upper deck floor beams, by doing all the applicable actions in accordance with Part 3.B.4. of the service bulletin. If no crack is found, repeat PO 00000 Frm 00007 Fmt 4700 Sfmt 4700 35991 the inspections at intervals not to exceed 1,000 flight cycles. (2) Accomplish detailed and open-hole HFEC inspections for cracking of the web, upper chord, and strap of the upper deck floor beams, by doing all the applicable actions in accordance with Part 3.B.5. of the service bulletin. If no crack is found, repeat the inspections at intervals not to exceed 5,000 flight cycles. Note 2: There is no terminating action currently available for the repetitive inspections required by this AD. Alternative Methods of Compliance (AMOCs) (k)(1) The Manager, Seattle ACO, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19. (2) An AMOC that provides an acceptable level of safety may be used for any repair required by this AD, if it is approved by a Boeing Company DER who has been authorized by the Manager, Seattle ACO, to make those findings. For a repair method to be approved, the approval must specifically refer to this AD. Material Incorporated by Reference (l) You must use Boeing Alert Service Bulletin 747–53A2443, dated May 9, 2002, 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 Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124–2207. 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 10, 2005. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 05–12002 Filed 6–21–05; 8:45 am] BILLING CODE 4910–13–P E:\FR\FM\22JNR1.SGM 22JNR1

Agencies

[Federal Register Volume 70, Number 119 (Wednesday, June 22, 2005)]
[Rules and Regulations]
[Pages 35989-35991]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-12002]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2004-19678; Directorate Identifier 2004-NM-62-AD; 
Amendment 39-14141; AD 2005-13-05]
RIN 2120-AA64


Airworthiness Directives; Boeing Model 747-400F Series Airplanes

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

ACTION: Final rule.

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

SUMMARY: The FAA is adopting a new airworthiness directive (AD) for 
certain Boeing Model 747-400F series airplanes. This AD requires 
initial detailed and open-hole high frequency eddy current inspections 
for cracking of the web, upper chord, and upper chord strap of the 
upper deck floor beams, and repair of any cracking. This AD also 
requires a preventive modification of the upper deck floor beams, and 
repetitive inspections for cracking after

[[Page 35990]]

accomplishing the modification. This AD is prompted by reports of 
fatigue cracking found on the upper deck floor beam to frame attachment 
points. We are issuing this AD to prevent fatigue cracks in the upper 
chord, upper chord strap, and the web of the upper deck floor beams and 
resultant failure of the floor beams. Failure of a floor beam could 
result in damage to critical flight control cables and wire bundles 
that pass through the floor beam, and consequent loss of 
controllability of the airplane. Failure of the floor beam also could 
result in the failure of the adjacent fuselage frames and skin, and 
consequent rapid decompression of the airplane.

DATES: This AD becomes effective July 27, 2005.
    The incorporation by reference of a certain publication listed in 
the AD is approved by the Director of the Federal Register as of July 
27, 2005.

ADDRESSES: For service information identified in this AD, contact 
Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124-
2207.
    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-2004-19678; the directorate 
identifier for this docket is 2004-NM-62-AD.

FOR FURTHER INFORMATION CONTACT: Ivan Li, Aerospace Engineer, Airframe 
Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 1601 Lind 
Avenue, SW., Renton, Washington 98055-4056; telephone (425) 917-6437; 
fax (425) 917-6590.

SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR part 39 
with an AD for certain Boeing Model 747-400F series airplanes. That 
action, published in the Federal Register on November 24, 2004 (69 FR 
68277), proposed to require initial detailed and open-hole high 
frequency eddy current inspections for cracking of the web, upper 
chord, and upper chord strap of the upper deck floor beams, and repair 
of any cracking. That action also proposed to require a preventive 
modification of the upper deck floor beams, and repetitive inspections 
for cracking after accomplishing the modification.

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 as proposed.

Costs of Compliance

    This AD affects about 53 airplanes worldwide and 13 airplanes of 
U.S. registry. The following table provides the estimated costs for 
U.S. operators to comply with this AD, depending on the airplane 
configuration:

                                                                     Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
                                                           Average                                                    Number of
                                                            labor                                                  affected U.S.-
              Action                     Work hours        rate per          Parts            Cost per  airplane     registered          Fleet cost
                                                             hour                                                     airplanes
--------------------------------------------------------------------------------------------------------------------------------------------------------
Pre-modification inspections.....  11...................        $65  $0...................  $715.................              13  $9,295
Modification/Inspections done      498 or 524...........         65  $13,554 or $14,874...  $45,924 or $48,934...              13  $597,012 or $636,142
 during modification.
Post-modification inspections....  66...................         65  $0...................  $4,290, per                        13  $55,770
                                                                                             inspection cycle.
--------------------------------------------------------------------------------------------------------------------------------------------------------

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. Subtitle VII, Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    We are issuing this rulemaking under the authority described in 
subtitle VII, part A, subpart III, section 44701, ``General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    We have determined that this AD will not have federalism 
implications under Executive Order 13132. This AD will not have a 
substantial direct effect on the States, on the relationship between 
the national government and the States, or on the distribution of power 
and responsibilities among the various levels of government.
    For the reasons discussed above, I certify that this AD:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866;
    (2) Is not a ``significant rule'' under DOT Regulatory Policies and 
Procedures (44 FR 11034, February 26, 1979); and
    (3) Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.
    We prepared a regulatory evaluation of the estimated costs to 
comply with this AD. 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:

[[Page 35991]]

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):

2005-13-05 Boeing: Amendment 39-14141. Docket No. FAA-2004-19678; 
Directorate Identifier 2004-NM-62-AD.

Effective Date

    (a) This AD becomes effective July 27, 2005.

Affected ADs

    (b) None.
    Applicability: (c) This AD applies to Model 747-400F series 
airplanes, certificated in any category, as listed in Boeing Alert 
Service Bulletin 747-53A2443, dated May 9, 2002.

Unsafe Condition

    (d) This AD was prompted by reports of fatigue cracking found on 
the upper deck floor beam to frame attachment points. We are issuing 
this AD to prevent fatigue cracks in the upper chord, upper chord 
strap, and web of the upper deck floor beams and the resultant 
failure of the floor beams. Failure of a floor beam could result in 
damage to critical flight control cables and wire bundles that pass 
through the floor beam, and consequent loss of controllability of 
the airplane. Failure of the floor beam also could result in the 
failure of the adjacent fuselage frames and skin, and consequent 
rapid decompression 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.

Service Bulletin Reference

    (f) For the purposes of this AD, the term ``service bulletin'' 
means the Accomplishment Instructions of Boeing Alert Service 
Bulletin 747-53A2443, dated May 9, 2002.

Inspections/Repair/Modification

    (g) Before the accumulation of 15,000 total flight cycles, or 
within 1,000 flight cycles after the effective date of this AD, 
whichever is later: Accomplish detailed and open-hole high frequency 
eddy current (HFEC) inspections for cracking of the web, upper 
chord, and upper chord strap of the upper deck floor beams, by doing 
all the applicable actions in accordance with Part 3.B.1. of the 
service bulletin.


    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.''


    (h) If any crack is found during any inspection required by 
paragraph (g) of this AD: Before further flight, accomplish the 
actions required by paragraph (h)(1) and (h)(2) of this AD.
    (1) Repair in accordance with the service bulletin; except where 
the service bulletin specifies to contact Boeing for appropriate 
action, before further flight, repair in accordance with a method 
approved by the Manager, Seattle Aircraft Certification Office 
(ACO), FAA; or according to data meeting the type certification 
basis of the airplane approved by a Boeing Company Designated 
Engineering Representative (DER) who has been authorized by the 
Manager, Seattle ACO, to make such findings. For a repair method to 
be approved by the Manager, Seattle ACO, as required by this 
paragraph, the Manager's approval letter must specifically reference 
this AD.
    (2) Accomplish the inspections and preventive modification of 
the floor beams by doing all the actions in accordance with Part 
3.B.2. or Part 3.B.3. of the service bulletin, as applicable. If any 
crack is found during any inspection, before further flight, repair 
as required by paragraph (h)(1) of this AD.
    (i) If no crack is found during any inspection required by 
paragraph (g) of this AD: Accomplish the actions required by either 
paragraph (i)(1) or (i)(2) of this AD, at the time specified.
    (1) Before further flight: Accomplish the inspections and 
preventive modification of the floor beam by doing all the actions 
in accordance with Part 3.B.2 or Part 3.B.3. of the service 
bulletin, as applicable. If the preventive modification is performed 
concurrently with the inspections required by paragraph (g) of this 
AD, the upper chord straps must be removed when performing the open-
hole HFEC inspection. If any crack is found during any inspection, 
before further flight, repair as required by paragraph (h)(1) of 
this AD.
    (2) Before the accumulation of 20,000 total flight cycles, or 
within 1,000 flight cycles after the effective date of this AD, 
whichever is later: Accomplish the inspections and preventive 
modification of the upper deck floor beams, by doing all the actions 
in accordance with Part 3.B.2. or 3.B.3. of the service bulletin, as 
applicable. If any crack is found during any inspection, before 
further flight, repair as required by paragraph (h)(1) of this AD.

Post-Modification Inspections

    (j) Within 15,000 flight cycles after accomplishing the 
applicable preventive modification required by paragraph (h)(2), 
(i)(1), or (i)(2) of this AD: Accomplish the inspections required by 
either paragraph (j)(1) or (j)(2) of this AD; if any crack is found 
during any inspection, before further flight, repair as required by 
paragraph (h)(1) of this AD.
    (1) Accomplish detailed and surface HFEC inspections for 
cracking of the web, upper chord, and upper chord strap of the upper 
deck floor beams, by doing all the applicable actions in accordance 
with Part 3.B.4. of the service bulletin. If no crack is found, 
repeat the inspections at intervals not to exceed 1,000 flight 
cycles.
    (2) Accomplish detailed and open-hole HFEC inspections for 
cracking of the web, upper chord, and strap of the upper deck floor 
beams, by doing all the applicable actions in accordance with Part 
3.B.5. of the service bulletin. If no crack is found, repeat the 
inspections at intervals not to exceed 5,000 flight cycles.

    Note 2: There is no terminating action currently available for 
the repetitive inspections required by this AD.

Alternative Methods of Compliance (AMOCs)

    (k)(1) The Manager, Seattle ACO, has the authority to approve 
AMOCs for this AD, if requested in accordance with the procedures 
found in 14 CFR 39.19.
    (2) An AMOC that provides an acceptable level of safety may be 
used for any repair required by this AD, if it is approved by a 
Boeing Company DER who has been authorized by the Manager, Seattle 
ACO, to make those findings. For a repair method to be approved, the 
approval must specifically refer to this AD.

Material Incorporated by Reference

    (l) You must use Boeing Alert Service Bulletin 747-53A2443, 
dated May 9, 2002, 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 Boeing Commercial Airplanes, P.O. 
Box 3707, Seattle, Washington 98124-2207. 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 10, 2005.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 05-12002 Filed 6-21-05; 8:45 am]
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