Airworthiness Directives; McDonnell Douglas Model DC-8-33, DC-8-51, DC-8-53, DC-8-55, DC-8F-54, DC-8F-55, DC-8-63, DC-8-62F, DC-8-63F, DC-8-71, DC-8-73, DC-8-71F, DC-8-72F, and DC-8-73F Airplanes, 5969-5971 [06-987]

Download as PDF 5969 Rules and Regulations Federal Register Vol. 71, No. 24 Monday, February 6, 2006 This section of the FEDERAL REGISTER contains regulatory documents having general applicability and legal effect, most of which are keyed to and codified in the Code of Federal Regulations, which is published under 50 titles pursuant to 44 U.S.C. 1510. The Code of Federal Regulations is sold by the Superintendent of Documents. Prices of new books are listed in the first FEDERAL REGISTER issue of each week. DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2005–22425; Directorate Identifier 2005–NM–066–AD; Amendment 39–14468; AD 2006–03–04] RIN 2120–AA64 Airworthiness Directives; McDonnell Douglas Model DC–8–33, DC–8–51, DC–8–53, DC–8–55, DC–8F–54, DC–8F– 55, DC–8–63, DC–8–62F, DC–8–63F, DC–8–71, DC–8–73, DC–8–71F, DC–8– 72F, and DC–8–73F Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. wwhite on PROD1PC65 with RULES AGENCY: 16:29 Feb 03, 2006 Jkt 208001 Examining the Docket You may examine the airworthiness directive (AD) docket on the Internet at http://dms.dot.gov or in person at the Docket 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 street address stated in the ADDRESSES section. Discussion SUMMARY: The FAA is adopting a new airworthiness directive (AD) for certain transport category airplanes, identified above. This AD requires repetitive inspections for cracks of the doorjamb corners of the main cabin cargo door, and repair if necessary. This AD also provides an optional preventive modification that extends certain repetitive intervals. This AD results from reports of cracks in the fuselage skin at the corners of the doorjamb for the main cabin cargo door. We are issuing this AD to detect and correct fatigue cracks in the fuselage skin, which could result in rapid decompression of the airplane. DATES: This AD becomes effective March 13, 2006. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD as of March 13, 2006. ADDRESSES: You may examine the AD docket on the Internet at http:// dms.dot.gov or in person at the Docket Management Facility, U.S. Department VerDate Aug<31>2005 of Transportation, 400 Seventh Street, SW., Nassif Building, room PL–401, Washington, DC. Contact Boeing Commercial Airplanes, Long Beach Division, 3855 Lakewood Boulevard, Long Beach, California 90846, Attention: Data and Service Management, Dept. C1–L5A (D800–0024), for service information identified in this AD. FOR FURTHER INFORMATION CONTACT: Jon Mowery, Aerospace Engineer, Airframe Branch, ANM–120L, FAA, Los Angeles Aircraft Certification Office, 3960 Paramount Boulevard, Lakewood, California 90712–4137; telephone (562) 627–5322; fax (562) 627–5210. SUPPLEMENTARY INFORMATION: refer to the inspections in Paragraph 1.E., Table 1, of Boeing Service Bulletin DC8–53–079, Revision 01, dated June 26, 2002, rather than using the current wording of paragraph (f). As proposed in the NPRM, paragraph (f) states: ‘‘Do detailed, high frequency eddy current, and radiographic inspections, as applicable * * * ,’’ which the commenter states can be interpreted to require that all inspection types be accomplished for the main cabin cargo door jamb corners. The commenter states that referring to Paragraph 1.E., Table 1, would clarify the intent of the required inspection techniques. The commenter also notes that this change would be consistent with the wording in two other ADs related to door jamb corners: AD 2000–20–08, amendment 39–11919, for passenger and service door jambs; and AD 2005–18–07, amendment 39–14247, for the lower cargo door jamb. We agree with the commenter. The requested change clarifies the intent of the inspection techniques, and is also consistent with the wording in similar ADs. We have revised paragraph (f) of the final rule to include this change. We have also deleted Note 1, which describes an inspection technique that is no longer mentioned in the AD. The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that would apply to certain McDonnell Douglas Model DC–8–33, DC–8–51, DC–8–53, DC–8–55, DC–8F–54, DC–8F–55, DC–8– 63, DC–8–62F, DC–8–63F, DC–8–71, DC–8–73, DC–8–71F, DC–8–72F, and DC–8–73F airplanes. That NPRM was published in the Federal Register on September 16, 2005 (70 FR 54674). That NPRM proposed to require repetitive inspections for cracks of the doorjamb corners of the main cabin cargo door, and repair if necessary. That NPRM also proposed an optional preventive modification that extends certain repetitive intervals. Clarification of Paragraph (g)(2) Comments Conclusion We provided the public the opportunity to participate in the development of this AD. We have considered the comment received. We have carefully reviewed the available data, including the comment received, and determined that air safety and the public interest require adopting the AD with the changes described previously. We have determined that these changes will neither increase the economic burden on any operator nor increase the scope of the AD. Request to Refer to Inspections in Service Bulletin The commenter requests that we change paragraph (f) of the NPRM to PO 00000 Frm 00001 Fmt 4700 Sfmt 4700 We have revised paragraph (g)(2) of this action to clarify that, for any corner where any crack is greater than 2.50 inches in length, the repair should be done using a method approved in accordance with the procedures specified in paragraph (k), rather than just in accordance with paragraph (k). Clarification of Alternative Method of Compliance (AMOC) Paragraph We have revised this action to clarify the appropriate procedure for notifying the principal inspector before using any approved AMOC on any airplane to which the AMOC applies. E:\FR\FM\06FER1.SGM 06FER1 5970 Federal Register / Vol. 71, No. 24 / Monday, February 6, 2006 / Rules and Regulations Costs of Compliance The following table provides the estimated costs for U.S. operators to There are about 225 airplanes of the affected design in the worldwide fleet. comply with this AD. The average labor rate is $65 per hour. ESTIMATED COSTS Action Parts Cost per airplane Number of U.S.-registered airplanes Fleet Cost 20 None ............................ 166 .............................. 80 $26,881 to $30,913 (per corner, depending on airplane configuration). $1,300, per inspection cycle. $32,081 to $36,113 ..... $215,800, per inspection cycle. Up to between $5,325,446 and $5,994,758 (for one corner). Work hours Inspection, per inspection cycle. Optional preventive modification (per corner). wwhite on PROD1PC65 with RULES Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, Section 106, describes the authority of the FAA Administrator. Subtitle VII, Aviation Programs, describes in more detail the scope of the Agency’s authority. We are issuing this rulemaking under the authority described in subtitle VII, part A, subpart III, Section 44701, ‘‘General requirements.’’ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings We have determined that this AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that this AD: (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866; (2) Is not a ‘‘significant rule’’ under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and (3) Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. We prepared a regulatory evaluation of the estimated costs to comply with this AD and placed it in the AD docket. See the ADDRESSES section for a location to examine the regulatory evaluation. VerDate Aug<31>2005 16:29 Feb 03, 2006 Jkt 208001 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 PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: I Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The Federal Aviation Administration (FAA) amends § 39.13 by adding the following new airworthiness directive (AD): I 2006–03–04 McDonnell Douglas: Amendment 39–14468. Docket No. FAA–2005–22425; Directorate Identifier 2005–NM–066–AD. Effective Date (a) This AD becomes effective March 13, 2006. Affected ADs (b) None. Applicability (c) This AD applies to McDonnell Douglas Model DC–8–33, DC–8–51, DC–8–53, DC–8– 55, DC–8F–54, DC–8F–55, DC–8–63, DC–8– 62F, DC–8–63F, DC–8–71, DC–8–73, DC–8– 71F, DC–8–72F, and DC–8–73F airplanes, certificated in any category; as identified in Boeing Service Bulletin DC8–53–079, Revision 01, dated June 26, 2002. Unsafe Condition (d) This AD results from reports of cracks in the fuselage skin at the corners of the doorjamb for the main cabin cargo door. We are issuing this AD to detect and correct fatigue cracks in the fuselage skin, which could result in rapid decompression of the airplane. PO 00000 Frm 00002 Fmt 4700 Sfmt 4700 Up to 166 .................... 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. Inspections (f) At the applicable time in paragraph (f)(1) or (f)(2) of this AD: Do the applicable inspections for cracking of the doorjamb corners of the main cabin cargo door in accordance with the Accomplishment Instructions of Boeing Service Bulletin DC8– 53–079, Revision 01, dated June 26, 2002; the applicable inspections are specified in Table 1 of Paragraph 1.E. ‘‘Compliance’’ of the service bulletin. Except as provided by paragraphs (g) and (h) of this AD, repeat the inspections thereafter at intervals not to exceed the applicable intervals specified in Table 1 of Paragraph 1.E. ‘‘Compliance’’ of the service bulletin. (1) For airplanes that have been converted from passenger to cargo under Amended Type Certificate Data Sheet 4A25, Notes 25 and 26, and McDonnell Douglas Supplemental Type Certificates SA3749WE and SA3403WE: Within 15,000 flight cycles after the conversion; or within 12 months after the effective date of this AD; whichever occurs later. (2) For airplanes that have not been converted from passenger to cargo: Before the accumulation of 15,000 total flight cycles, or within 3,000 flight cycles after the effective date of this AD, whichever occurs later. Corrective Actions and New Repetitive Intervals (g) If any crack is found during any inspection required by this AD, before further flight: Do the applicable action in paragraph (g)(1) or (g)(2) of this AD in accordance with the Accomplishment Instructions of Boeing Service Bulletin DC8–53–079, Revision 01, dated June 26, 2002. (1) For any corner where all cracks are 2.50 inches or less in length, install an external doubler in accordance with the service bulletin: Before the accumulation of 17,000 flight cycles after the installation, do the next inspection of that corner as specified in paragraph (f) of this AD. Repeat the inspections in paragraph (f) of this AD for that corner thereafter at intervals not to exceed 4,400 flight cycles. (2) For any corner where any crack is greater than 2.50 inches in length, repair the E:\FR\FM\06FER1.SGM 06FER1 Federal Register / Vol. 71, No. 24 / Monday, February 6, 2006 / Rules and Regulations crack using a method approved in accordance with the procedures specified in paragraph (k) of this AD. Optional Preventive Modification (h) Installing an external doubler on a corner in accordance with the Accomplishment Instructions of Boeing Service Bulletin DC8–53–079, Revision 01, dated June 26, 2002, terminates the repetitive inspection intervals of paragraph (f) of this AD for that corner. Before the accumulation of 17,000 flight cycles after the installation: Do the next inspection of that corner, as specified in paragraph (f) of this AD. Repeat the inspections in paragraph (f) of this AD for that corner thereafter at intervals not to exceed 4,400 flight cycles. No Reporting Required (i) Although the service bulletin referenced in this AD specifies to submit certain information to the manufacturer, this AD does not include that requirement. Actions Accomplished In Accordance With Previous Issue of Service Bulletin (j) Actions accomplished before the effective date of this AD in accordance with McDonnell Douglas Service Bulletin C8–53– 079, dated January 31, 2001, are acceptable for compliance with the corresponding action in this AD. wwhite on PROD1PC65 with RULES Alternative Methods of Compliance (AMOCs) (k)(1) The Manager, Los Angeles 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. (2) Before using any AMOC approved in accordance with § 39.19 on any airplane to which the AMOC applies, notify the appropriate principal inspector in the FAA Flight Standards Certificate Holding District Office. (3) An AMOC that provides an acceptable level of safety may be used for any repair required by this AD, if it is approved by an Authorized Representative for the Boeing Commercial Airplanes Delegation Option Authorization Organization who has been authorized by the Manager, Los Angeles ACO, to make those findings. For a repair method to be approved, the repair must meet the certification basis of the airplane and 14 CFR 25.571, Amendment 45, and the approval must specifically refer to this AD. (4) Inspections required by this AD of specified areas of Principal Structural Element (PSE) 53.08.044 are acceptable for compliance with the applicable requirements of paragraphs (a) and (b) of AD 93–01–15, amendment 39–8469 (58 FR 5576, January 22, 1993). The remaining areas of the affected PSEs must be inspected and repaired as applicable, in accordance with AD 93–01–15. Material Incorporated by Reference (l) You must use Boeing Service Bulletin DC8–53–079, Revision 01, dated June 26, 2002, to perform the actions that are required by this AD, unless the AD specifies otherwise. The Director of the Federal Register approved the incorporation by reference of this document in accordance VerDate Aug<31>2005 16:29 Feb 03, 2006 Jkt 208001 with 5 U.S.C. 552(a) and 1 CFR part 51. Contact Boeing Commercial Airplanes, Long Beach Division, 3855 Lakewood Boulevard, Long Beach, California 90846, Attention: Data and Service Management, Dept. C1–L5A (D800–0024), for a copy of this service information. You may review copies at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street, SW., room PL–401, Nassif Building, Washington, DC; on the Internet at http:// dms.dot.gov; or at 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 January 24, 2006. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 06–987 Filed 2–3–06; 8:45 am] BILLING CODE 4910–13–P 5971 stabilizer, sparking of metal parts and debris from detached and damaged float valves, or a buildup of static electricity, which could result in ignition of fuel vapors and consequent fire or explosion. This AD becomes effective March 13, 2006. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the AD as of March 13, 2006. DATES: You may examine the 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., Nassif Building, Room PL–401, Washington, DC. Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France, for service information identified in this AD. ADDRESSES: Tim Backman, Aerospace Engineer, International Branch, ANM–116, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98055–4056; telephone (425) 227–2797; fax (425) 227–1149. FOR FURTHER INFORMATION CONTACT: DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2005–21702; Directorate Identifier 2005–NM–024–AD; Amendment 39–14473; AD 2006–03–09] SUPPLEMENTARY INFORMATION: RIN 2120–AA64 You may examine the airworthiness directive (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 street address stated in the ADDRESSES section. Airworthiness Directives; Airbus Model A330–200 and –300 Series Airplanes, A340–200 and –300 Series Airplanes, and A340–541 and –642 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 Airbus Model A330–200 and –300 series airplanes, A340–200 and –300 series airplanes, and A340–541 and –642 airplanes. This AD requires repetitive borescope inspections of the left and right fuel tanks of the trimmable horizontal stabilizers (trim tanks) for detached or damaged float valves; related investigative/corrective actions if necessary; and the eventual replacement of all float valves in the left and right trim tanks with new, improved float valves, which terminates the need for the repetitive inspections. This AD also requires repetitive replacement of certain new, improved float valves. This AD results from reports of detached and damaged float valves in the trim tanks. We are issuing this AD to prevent, in the event of a lightning strike to the horizontal PO 00000 Frm 00003 Fmt 4700 Sfmt 4700 Examining the Docket Discussion The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that would apply to certain Airbus Model A330 and A340 series airplanes. That NPRM was published in the Federal Register on June 29, 2005 (70 FR 37296). That NPRM proposed to require repetitive borescope inspections of the left and right fuel tanks of the trimmable horizontal stabilizers (trim tanks) for detached or damaged float valves; related investigative/corrective actions if necessary; and the eventual replacement of all float valves in the left and right trim tanks with new, improved float valves, which terminates the need for the repetitive inspections. That NPRM also proposed to require repetitive replacement of certain new, improved float valves. E:\FR\FM\06FER1.SGM 06FER1

Agencies

[Federal Register Volume 71, Number 24 (Monday, February 6, 2006)]
[Rules and Regulations]
[Pages 5969-5971]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 06-987]



========================================================================
Rules and Regulations
                                                Federal Register
________________________________________________________________________

This section of the FEDERAL REGISTER contains regulatory documents 
having general applicability and legal effect, most of which are keyed 
to and codified in the Code of Federal Regulations, which is published 
under 50 titles pursuant to 44 U.S.C. 1510.

The Code of Federal Regulations is sold by the Superintendent of Documents. 
Prices of new books are listed in the first FEDERAL REGISTER issue of each 
week.

========================================================================


Federal Register / Vol. 71, No. 24 / Monday, February 6, 2006 / Rules 
and Regulations

[[Page 5969]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-22425; Directorate Identifier 2005-NM-066-AD; 
Amendment 39-14468; AD 2006-03-04]
RIN 2120-AA64


Airworthiness Directives; McDonnell Douglas Model DC-8-33, DC-8-
51, DC-8-53, DC-8-55, DC-8F-54, DC-8F-55, DC-8-63, DC-8-62F, DC-8-63F, 
DC-8-71, DC-8-73, DC-8-71F, DC-8-72F, and DC-8-73F 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 transport category airplanes, identified above.
    This AD requires repetitive inspections for cracks of the doorjamb 
corners of the main cabin cargo door, and repair if necessary. This AD 
also provides an optional preventive modification that extends certain 
repetitive intervals. This AD results from reports of cracks in the 
fuselage skin at the corners of the doorjamb for the main cabin cargo 
door. We are issuing this AD to detect and correct fatigue cracks in 
the fuselage skin, which could result in rapid decompression of the 
airplane.

DATES: This AD becomes effective March 13, 2006.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in the AD as of March 13, 
2006.

ADDRESSES: You may examine the 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., Nassif Building, 
room PL-401, Washington, DC.
    Contact Boeing Commercial Airplanes, Long Beach Division, 3855 
Lakewood Boulevard, Long Beach, California 90846, Attention: Data and 
Service Management, Dept. C1-L5A (D800-0024), for service information 
identified in this AD.

FOR FURTHER INFORMATION CONTACT: Jon Mowery, Aerospace Engineer, 
Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification 
Office, 3960 Paramount Boulevard, Lakewood, California 90712-4137; 
telephone (562) 627-5322; fax (562) 627-5210.

SUPPLEMENTARY INFORMATION: 

Examining the Docket

    You may examine the airworthiness directive (AD) docket on the 
Internet at http://dms.dot.gov or in person at the Docket 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 street address stated in the ADDRESSES section.

Discussion

    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 
CFR part 39 to include an AD that would apply to certain McDonnell 
Douglas Model DC-8-33, DC-8-51, DC-8-53, DC-8-55, DC-8F-54, DC-8F-55, 
DC-8-63, DC-8-62F, DC-8-63F, DC-8-71, DC-8-73, DC-8-71F, DC-8-72F, and 
DC-8-73F airplanes. That NPRM was published in the Federal Register on 
September 16, 2005 (70 FR 54674). That NPRM proposed to require 
repetitive inspections for cracks of the doorjamb corners of the main 
cabin cargo door, and repair if necessary. That NPRM also proposed an 
optional preventive modification that extends certain repetitive 
intervals.

Comments

    We provided the public the opportunity to participate in the 
development of this AD. We have considered the comment received.

Request to Refer to Inspections in Service Bulletin

    The commenter requests that we change paragraph (f) of the NPRM to 
refer to the inspections in Paragraph 1.E., Table 1, of Boeing Service 
Bulletin DC8-53-079, Revision 01, dated June 26, 2002, rather than 
using the current wording of paragraph (f). As proposed in the NPRM, 
paragraph (f) states: ``Do detailed, high frequency eddy current, and 
radiographic inspections, as applicable * * * ,'' which the commenter 
states can be interpreted to require that all inspection types be 
accomplished for the main cabin cargo door jamb corners. The commenter 
states that referring to Paragraph 1.E., Table 1, would clarify the 
intent of the required inspection techniques. The commenter also notes 
that this change would be consistent with the wording in two other ADs 
related to door jamb corners: AD 2000-20-08, amendment 39-11919, for 
passenger and service door jambs; and AD 2005-18-07, amendment 39-
14247, for the lower cargo door jamb.
    We agree with the commenter. The requested change clarifies the 
intent of the inspection techniques, and is also consistent with the 
wording in similar ADs. We have revised paragraph (f) of the final rule 
to include this change. We have also deleted Note 1, which describes an 
inspection technique that is no longer mentioned in the AD.

Clarification of Paragraph (g)(2)

    We have revised paragraph (g)(2) of this action to clarify that, 
for any corner where any crack is greater than 2.50 inches in length, 
the repair should be done using a method approved in accordance with 
the procedures specified in paragraph (k), rather than just in 
accordance with paragraph (k).

Clarification of Alternative Method of Compliance (AMOC) Paragraph

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

Conclusion

    We have carefully reviewed the available data, including the 
comment received, and determined that air safety and the public 
interest require adopting the AD with the changes described previously. 
We have determined that these changes will neither increase the 
economic burden on any operator nor increase the scope of the AD.

[[Page 5970]]

Costs of Compliance

    There are about 225 airplanes of the affected design in the 
worldwide fleet. The following table provides the estimated costs for 
U.S. operators to comply with this AD. The average labor rate is $65 
per hour.

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                Number of U.S.-
           Action               Work hours         Parts           Cost per        registered       Fleet Cost
                                                                   airplane        airplanes
----------------------------------------------------------------------------------------------------------------
Inspection, per inspection                20  None...........  $1,300, per      166............  $215,800, per
 cycle.                                                         inspection                        inspection
                                                                cycle.                            cycle.
Optional preventive                       80  $26,881 to       $32,081 to       Up to 166......  Up to between
 modification (per corner).                    $30,913 (per     $36,113.                          $5,325,446 and
                                               corner,                                            $5,994,758
                                               depending on                                       (for one
                                               airplane                                           corner).
                                               configuration).
----------------------------------------------------------------------------------------------------------------

Authority for This Rulemaking

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

Regulatory Findings

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

List of Subjects in 14 CFR Part 39

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

Adoption of the Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

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

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


Sec.  39.13  [Amended]

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

2006-03-04 McDonnell Douglas: Amendment 39-14468. Docket No. FAA-
2005-22425; Directorate Identifier 2005-NM-066-AD.

Effective Date

    (a) This AD becomes effective March 13, 2006.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to McDonnell Douglas Model DC-8-33, DC-8-51, 
DC-8-53, DC-8-55, DC-8F-54, DC-8F-55, DC-8-63, DC-8-62F, DC-8-63F, 
DC-8-71, DC-8-73, DC-8-71F, DC-8-72F, and DC-8-73F airplanes, 
certificated in any category; as identified in Boeing Service 
Bulletin DC8-53-079, Revision 01, dated June 26, 2002.

Unsafe Condition

    (d) This AD results from reports of cracks in the fuselage skin 
at the corners of the doorjamb for the main cabin cargo door. We are 
issuing this AD to detect and correct fatigue cracks in the fuselage 
skin, which could result in 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.

Inspections

    (f) At the applicable time in paragraph (f)(1) or (f)(2) of this 
AD: Do the applicable inspections for cracking of the doorjamb 
corners of the main cabin cargo door in accordance with the 
Accomplishment Instructions of Boeing Service Bulletin DC8-53-079, 
Revision 01, dated June 26, 2002; the applicable inspections are 
specified in Table 1 of Paragraph 1.E. ``Compliance'' of the service 
bulletin. Except as provided by paragraphs (g) and (h) of this AD, 
repeat the inspections thereafter at intervals not to exceed the 
applicable intervals specified in Table 1 of Paragraph 1.E. 
``Compliance'' of the service bulletin.
    (1) For airplanes that have been converted from passenger to 
cargo under Amended Type Certificate Data Sheet 4A25, Notes 25 and 
26, and McDonnell Douglas Supplemental Type Certificates SA3749WE 
and SA3403WE: Within 15,000 flight cycles after the conversion; or 
within 12 months after the effective date of this AD; whichever 
occurs later.
    (2) For airplanes that have not been converted from passenger to 
cargo: Before the accumulation of 15,000 total flight cycles, or 
within 3,000 flight cycles after the effective date of this AD, 
whichever occurs later.

Corrective Actions and New Repetitive Intervals

    (g) If any crack is found during any inspection required by this 
AD, before further flight: Do the applicable action in paragraph 
(g)(1) or (g)(2) of this AD in accordance with the Accomplishment 
Instructions of Boeing Service Bulletin DC8-53-079, Revision 01, 
dated June 26, 2002.
    (1) For any corner where all cracks are 2.50 inches or less in 
length, install an external doubler in accordance with the service 
bulletin: Before the accumulation of 17,000 flight cycles after the 
installation, do the next inspection of that corner as specified in 
paragraph (f) of this AD. Repeat the inspections in paragraph (f) of 
this AD for that corner thereafter at intervals not to exceed 4,400 
flight cycles.
    (2) For any corner where any crack is greater than 2.50 inches 
in length, repair the

[[Page 5971]]

crack using a method approved in accordance with the procedures 
specified in paragraph (k) of this AD.

Optional Preventive Modification

    (h) Installing an external doubler on a corner in accordance 
with the Accomplishment Instructions of Boeing Service Bulletin DC8-
53-079, Revision 01, dated June 26, 2002, terminates the repetitive 
inspection intervals of paragraph (f) of this AD for that corner. 
Before the accumulation of 17,000 flight cycles after the 
installation: Do the next inspection of that corner, as specified in 
paragraph (f) of this AD. Repeat the inspections in paragraph (f) of 
this AD for that corner thereafter at intervals not to exceed 4,400 
flight cycles.

No Reporting Required

    (i) Although the service bulletin referenced in this AD 
specifies to submit certain information to the manufacturer, this AD 
does not include that requirement.

Actions Accomplished In Accordance With Previous Issue of Service 
Bulletin

    (j) Actions accomplished before the effective date of this AD in 
accordance with McDonnell Douglas Service Bulletin C8-53-079, dated 
January 31, 2001, are acceptable for compliance with the 
corresponding action in this AD.

Alternative Methods of Compliance (AMOCs)

    (k)(1) The Manager, Los Angeles 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.
    (2) Before using any AMOC approved in accordance with Sec.  
39.19 on any airplane to which the AMOC applies, notify the 
appropriate principal inspector in the FAA Flight Standards 
Certificate Holding District Office.
    (3) An AMOC that provides an acceptable level of safety may be 
used for any repair required by this AD, if it is approved by an 
Authorized Representative for the Boeing Commercial Airplanes 
Delegation Option Authorization Organization who has been authorized 
by the Manager, Los Angeles ACO, to make those findings. For a 
repair method to be approved, the repair must meet the certification 
basis of the airplane and 14 CFR 25.571, Amendment 45, and the 
approval must specifically refer to this AD.
    (4) Inspections required by this AD of specified areas of 
Principal Structural Element (PSE) 53.08.044 are acceptable for 
compliance with the applicable requirements of paragraphs (a) and 
(b) of AD 93-01-15, amendment 39-8469 (58 FR 5576, January 22, 
1993). The remaining areas of the affected PSEs must be inspected 
and repaired as applicable, in accordance with AD 93-01-15.

Material Incorporated by Reference

    (l) You must use Boeing Service Bulletin DC8-53-079, Revision 
01, dated June 26, 2002, to perform the actions that are required by 
this AD, unless the AD specifies otherwise. The Director of the 
Federal Register approved the incorporation by reference of this 
document in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. 
Contact Boeing Commercial Airplanes, Long Beach Division, 3855 
Lakewood Boulevard, Long Beach, California 90846, Attention: Data 
and Service Management, Dept. C1-L5A (D800-0024), for a copy of this 
service information. You may review copies at the Docket Management 
Facility, U.S. Department of Transportation, 400 Seventh Street, 
SW., room PL-401, Nassif Building, Washington, DC; on the Internet 
at http://dms.dot.gov; or at 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 January 24, 2006.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 06-987 Filed 2-3-06; 8:45 am]
BILLING CODE 4910-13-P