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, 54674-54677 [05-18401]

Download as PDF 54674 Federal Register / Vol. 70, No. 179 / Friday, September 16, 2005 / Proposed Rules by adding the following new airworthiness directive (AD): British Aerospace Airbus Limited: Docket No. FAA–2005–22427; Directorate Identifier 2004–NM–263–AD. Comments Due Date (a) The FAA must receive comments on this AD action by October 17, 2005. Affected ADs (b) None. Applicability (c) This AD applies to all British Aerospace Model BAC 1–11 200 and 400 series airplanes, certificated in any category. Unsafe Condition (d) This AD results from fuel system reviews conducted by the manufacturer. We are issuing this AD to ensure that the flightcrew and maintenance personnel are advised of procedures pertaining to the safety of the fuel system. These procedures are needed to prevent potential ignition sources inside the fuel system, which, in combination with flammable fuel vapors, could result in a fuel tank explosion and consequent loss 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. Airplane Flight Manual and Maintenance Program Revisions (f) Within 3 months after the effective date of this AD, do the actions specified in paragraphs (f)(1) and (f)(2) of this AD to improve the safety of the fuel system, in accordance with the Accomplishment Instructions of Airbus UK BAC One-Eleven Alert Service Bulletin 28–A–PM6057, Issue 1, dated May 10, 2004. (1) Revise the airplane flight manual to include the applicable amendments advising the flightcrew of appropriate procedures to check for proper operation of the fuel system, and to address tripped circuit breakers, failure of a fuel pump in flight, and operations in a low-fuel situation, as specified in Table 2 (under Section 4.11) of the service bulletin. Note 1: The actions required by paragraph (f)(1) of this AD may be done by inserting a copy of the applicable advance amendment bulletins (AABs) specified in Table 2 of Airbus UK BAC One-Eleven Alert Service Bulletin 28–A–PM6057, Issue 1, dated May 10, 2004, into the AFM. When information identical to that in the applicable AABs has been included in the general revisions of the AFM, the AABs no longer need to be inserted into the AFM. (2) Revise the FAA-approved maintenance program to include all repetitive maintenance tasks specified in Table 1 (under Section 4.10.2.) of the service bulletin. Then, thereafter, comply with the requirements of these maintenance tasks at the interval specified in Table 1 of the service bulletin; except for airplanes that operate fewer than a total of 1,250 flight hours per VerDate Aug<31>2005 18:38 Sep 15, 2005 Jkt 205001 year, accomplish the requirements of these maintenance tasks at the earlier of the times specified in columns 2 and 3 of Table 1 of the service bulletin. Where Table 1 of the service bulletin specifies a repetitive interval in ‘‘hours,’’ for the purposes of this AD, this means ‘‘flight hours.’’ Any applicable corrective actions must be done before further flight. Note 2: After revising the maintenance program to include the required periodic maintenance tasks according to paragraph (f)(2) of this AD, operators do not need to make a maintenance log entry to show compliance with this AD every time those maintenance tasks are accomplished thereafter. Alternative Methods of Compliance (AMOCs) (g) The Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19. Related Information (h) British airworthiness directive G–2004– 0012, dated June 21, 2004, also addresses the subject of this AD. Issued in Renton, Washington, on September 7, 2005. Kalene C. Yanamura, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 05–18402 Filed 9–15–05; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2005–22425; Directorate Identifier 2005–NM–066–AD] 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: Notice of proposed rulemaking (NPRM). AGENCY: SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) for certain transport category airplanes, identified above. This proposed AD would require repetitive inspections for cracks of the doorjamb corners of the main cargo door, and repair if necessary. This proposed AD also provides an optional preventive modification that extends certain repetitive intervals. This PO 00000 Frm 00017 Fmt 4702 Sfmt 4702 proposed AD results from reports of cracks in the fuselage skin at the corners of the doorjamb for the main cabin cargo door. We are proposing this AD to detect and correct fatigue cracks in the fuselage skin, which could result in rapid decompression of the airplane. DATES: We must receive comments on this proposed AD by October 31, 2005. ADDRESSES: Use one of the following addresses to submit comments on this proposed AD. • DOT Docket Web site: Go to https://dms.dot.gov and follow the instructions for sending your comments electronically. • Government-Wide Rulemaking Web Site: Go to https://www.regulations.gov and follow the instructions for sending your comments electronically. • Mail: Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street SW., Nassif Building, room PL–401, Washington, DC 20590. • Fax: (202) 493–2251. • Hand Delivery: Room PL–401 on the plaza level of the Nassif Building, 400 Seventh Street SW., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. Contact Boeing Commercial Airplanes, Long Beach Division, 3855 Lakewood Boulevard, Long Beach, California 90846, Attention: Data and Service Management, Dept. C1–L5A (D800–0024), for the service information identified in this proposed 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: Comments Invited We invite you to submit any relevant written data, views, or arguments regarding this proposed AD. Send your comments to an address listed in the ADDRESSES section. Include the docket number ‘‘FAA–2005–22425; Directorate Identifier 2005–NM–066–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the proposed AD. We will consider all comments received by the closing date and may amend the proposed AD in light of those comments. We will post all comments we receive, without change, to https:// dms.dot.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact with FAA E:\FR\FM\16SEP1.SGM 16SEP1 Federal Register / Vol. 70, No. 179 / Friday, September 16, 2005 / Proposed Rules Document (SID).’’ That AD also requires reporting results of inspections to McDonnell Douglas, and repairing any cracked structure detected during the inspections. personnel concerning this proposed AD. Using the search function of that web site, anyone can find and read the comments in any of our dockets, including the name of the individual who sent the comment (or signed the comment on behalf of an association, business, labor union, etc.). You may review DOT’s complete Privacy Act Statement in the Federal Register published on April 11, 2000 (65 FR 19477–78), or you may visit https:// dms.dot.gov. Relevant Service Information We have reviewed Boeing Service Bulletin DC8–53–079, Revision 01, dated June 26, 2002. The service bulletin describes procedures for repetitive inspections for cracks of the doorjamb corners of the main cargo door. The inspections include radiographic, high frequency eddy current (HFEC), and visual (optically aided) inspections. Each inspection type is repeated in combination (e.g., radiographic and HFEC together) at varying intervals that range from 4,937 landings to 11,325 landings depending on the type of inspection. These intervals are described in Table 1 of paragraph 1.E. ‘‘Compliance’’ of the service bulletin. If any crack is found that is 2.50 inches in length or less, the service bulletin describes procedures for repairing the fuselage skin and installing an external doubler. If any crack is found that is greater than 2.50 inches in length, the service bulletin specifies contacting the manufacturer for repair instructions and for reporting certain information. The service bulletin also gives procedures for a preventive modification of installing an external doubler at the corner of the main cabin cargo doorjamb. After any modification or repair, the service bulletin specifies that operators should inspect again for cracks of the modified or repaired doorjamb corner within 17,000 landings after doing the modification or repair, and then repeat the inspection at intervals not to exceed 4,400 landings. Accomplishing the actions specified in the service information is intended to adequately address the unsafe condition. The inspection program in Revision 01 of the service bulletin is an alternative method of compliance (AMOC) for the requirements of Examining the Docket You may examine the AD docket on the Internet at https://dms.dot.gov, or in person at the Docket Management Facility office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Management Facility office (telephone (800) 647–5227) is located on the plaza level of the Nassif Building at the DOT street address stated in the ADDRESSES section. Comments will be available in the AD docket shortly after the Docket Management System receives them. Discussion We have received reports of cracks in the fuselage skin at the corners of the doorjamb for the main cabin cargo door on McDonnell Douglas Model DC–8– 71F airplanes. Cracks were found on airplanes that had accumulated 14,600 landings. The manufacturer’s investigation showed that the cracks resulted from fatigue stress. Fatigue cracks, if not corrected, could progress and result in rapid decompression of the airplane. Other Relevant Rulemaking On January 11, 1993, we issued AD 93–01–15, amendment 39–8469 (58 FR 5576, January 22, 1993). We issued that AD to ensure the continuing structural integrity of McDonnell Douglas Model DC–8 airplanes. That AD requires revising the FAA-approved maintenance inspection program, which provides for inspection of the Principal Structural Elements (PSEs) identified in McDonnell Douglas Report No. L26– 011, ‘‘DC–8 Supplemental Inspection 54675 paragraphs (a) and (b) of AD 93–01–15 for the specified areas of PSE 53.08.044. FAA’s Determination and Requirements of the Proposed AD We have evaluated all pertinent information and identified an unsafe condition that is likely to exist or develop on other airplanes of this same type design. For this reason, we are proposing this AD, which would require accomplishing the actions specified in the service information described previously, except as discussed under ‘‘Differences Between the Proposed AD and the Service Bulletin.’’ Differences Between the Proposed AD and the Service Bulletin The service bulletin specifies to contact the manufacturer for instructions on how to repair certain conditions, but this proposed AD would require repairing those conditions in one of the following ways: • Using a method that we approve; or • Using data that meet the certification basis of the airplane, and that have been approved by an Authorized Representative for the Boeing Commercial Airplanes Delegation Option Authorization (DOA) Organization whom we have authorized to make those findings. Operators should note that, although the Accomplishment Instructions of the service bulletin describe procedures for submitting certain information to the manufacturer, this AD would not require that action. Clarification of Inspection Language In this proposed AD, the ‘‘visual (optically aided)’’ inspection specified in the Boeing service bulletin is referred to as a ‘‘detailed inspection.’’ We have included the definition for a detailed inspection in a note in the proposed AD. 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 proposed AD. ESTIMATED COSTS Work hours Action Inspection, per inspection cycle. Optional preventive modification (per corner). VerDate Aug<31>2005 Average labor rate per hour 20 $65 80 65 18:38 Sep 15, 2005 Jkt 205001 Parts Cost per airplane Number of U.S.-registered airplanes None ......................... $1,300, per inspection cycle. $32,081 to $36,113 .. 166 ........................... $26,881 to $30,913 (per corner, depending on airplane configuration). PO 00000 Frm 00018 Fmt 4702 Sfmt 4702 Up to 166 ................. E:\FR\FM\16SEP1.SGM 16SEP1 Fleet cost $215,800, per inspection cycle. Up to between $5,325,446 and $5,994,758 (for one corner). 54676 Federal Register / Vol. 70, No. 179 / Friday, September 16, 2005 / Proposed 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 proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would not have a substantial direct effect on the States, on the relationship between the national Government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that the proposed regulation: 1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866; 2. Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and 3. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. We prepared a regulatory evaluation of the estimated costs to comply with this proposed AD and placed it in the AD docket. See the ADDRESSES section for a location to examine the regulatory evaluation. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: VerDate Aug<31>2005 18:38 Sep 15, 2005 Jkt 205001 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): McDonnell Douglas: Docket No. FAA–2005– 22425; Directorate Identifier 2005–NM– 066–AD. Comments Due Date (a) The FAA must receive comments on this AD action by October 31, 2005. 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 detailed, high frequency eddy current, and radiographic inspections, as applicable, for cracks of the doorjamb corners of the main cargo door in accordance with the Accomplishment Instructions of Boeing Service Bulletin DC8– 53–079, Revision 01, dated June 26, 2002. Except as provided by paragraph (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. 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 PO 00000 Frm 00019 Fmt 4702 Sfmt 4702 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.’’ 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 crack using a method approved in accordance with 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 Boeing Service Bulletin DC8–53–079, 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) 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 E:\FR\FM\16SEP1.SGM 16SEP1 Federal Register / Vol. 70, No. 179 / Friday, September 16, 2005 / Proposed Rules the certification basis of the airplane and 14 CFR 25.571, Amendment 45, and the approval must specifically refer to this AD. (3) 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. Issued in Renton, Washington, on September 7, 2005. Kalene C. Yanamura, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 05–18401 Filed 9–15–05; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2005–22426; Directorate Identifier 2005–NM–105–AD] RIN 2120–AA64 Airworthiness Directives; Boeing Model 747–100, 747–100B, 747–100B SUD, 747–200B, 747–200C, 747–300, 747–400, 747–400D, and 747SR Series Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Notice of proposed rulemaking (NPRM). AGENCY: SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) for all Boeing Model 747–100, 747–100B, 747– 100B SUD, 747–200B, 747–200C, 747– 300, 747–400, 747–400D, and 747SR series airplanes. This proposed AD would require a one-time inspection to determine whether any steel doubler (small or large) is installed at the lower forward and upper aft corners of the fuselage cutout at main entry doors (MEDs) number 3. Depending on the results of this inspection, this proposed AD also would require repetitive inspections for cracks of the skin, bearstrap, and small steel doubler (if installed) at the applicable corner or corners of the fuselage cutouts, and related investigative/corrective actions if necessary. This proposed AD also would provide the optional terminating action for the repetitive inspections of installing a large steel doubler at the affected corners. This proposed AD is prompted by reports of cracks in the skin and bearstrap at the upper aft corner and at the lower forward corner VerDate Aug<31>2005 18:38 Sep 15, 2005 Jkt 205001 of the fuselage cutout at MEDs number 3. We are proposing this AD to detect and correct cracks in the skin, bearstrap, and small steel doubler (if installed), which could propagate and result in rapid decompression of the airplane. DATES: We must receive comments on this proposed AD by October 31, 2005. ADDRESSES: Use one of the following addresses to submit comments on this proposed AD. • DOT Docket Web Site: Go to https://dms.dot.gov and follow the instructions for sending your comments electronically. • Government-Wide Rulemaking Web Site: Go to https://www.regulations.gov and follow the instructions for sending your comments electronically. • Mail: Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street SW., Nassif Building, room PL–401, Washington, DC 20590. • By fax: (202) 493–2251. • Hand Delivery: Room PL–401 on the plaza level of the Nassif Building, 400 Seventh Street SW., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this proposed AD, contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124–2207. You can examine the contents of this AD docket on the Internet at https:// dms.dot.gov, or in person at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street SW., room PL–401, on the plaza level of the Nassif Building, Washington, DC. This docket number is FAA–2005– 22426; the directorate identifier for this docket is 2005–NM–105–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: Comments Invited We invite you to submit any relevant written data, views, or arguments regarding this proposed AD. Send your comments to an address listed under ADDRESSES. Include ‘‘Docket No. FAA– 2005–22426; Directorate Identifier 2005–NM–105–AD’’ in the subject line of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the proposed AD. We will consider all comments submitted by the closing date and may amend the proposed AD in light of those comments. PO 00000 Frm 00020 Fmt 4702 Sfmt 4702 54677 We will post all comments we receive, without change, to https:// dms.dot.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact with FAA personnel concerning this proposed AD. Using the search function of that website, anyone can find and read the comments in any of our dockets, including the name of the individual who sent the comment (or signed the comment on behalf of an association, business, labor union, etc.). You can review DOT’s complete Privacy Act Statement in the Federal Register published on April 11, 2000 (65 FR 19477–78), or you can visit https:// dms.dot.gov. Examining the Docket You can examine the AD docket on the Internet at https://dms.dot.gov, or in person at the Docket Management Facility office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Management Facility office (telephone (800) 647–5227) is located on the plaza level of the Nassif Building at the DOT street address stated in the ADDRESSES section. Comments will be available in the AD docket shortly after the Docket Management System (DMS) receives them. Discussion We have received a report indicating that seven operators of the affected airplanes have found cracks in the skin and bearstrap at the upper aft corner of the fuselage cutout at main entry doors (MEDs) number 3. These cracks, which were between 0.6 inch and 2.5 inches in length, were found on airplanes that had accumulated between 12,140 and 23,927 flight cycles. We have received other reports indicating that some operators also found cracks in the skin and bearstrap at the lower forward corner of the fuselage cutout at MEDs number 3. These cracks were between 0.5 inch and 4.0 inches in length, and were found on airplanes that had accumulated between 11,986 and 23,083 flight cycles. Cracks in the skin, bearstrap, and small steel doubler, if not detected and corrected, could propagate and result in rapid decompression of the airplane. Other Relevant Rulemaking On December 8, 1992, we issued AD 92–27–04, amendment 39–8437 (57 FR 59801, December 16, 1992) for certain Boeing Model 747 series airplanes. [A correction of that AD was published in the Federal Register on February 17, 1993 (58 FR 8693)]. We issued that AD to prevent the structural degradation of E:\FR\FM\16SEP1.SGM 16SEP1

Agencies

[Federal Register Volume 70, Number 179 (Friday, September 16, 2005)]
[Proposed Rules]
[Pages 54674-54677]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-18401]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-22425; Directorate Identifier 2005-NM-066-AD]
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: Notice of proposed rulemaking (NPRM).

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

SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) 
for certain transport category airplanes, identified above. This 
proposed AD would require repetitive inspections for cracks of the 
doorjamb corners of the main cargo door, and repair if necessary. This 
proposed AD also provides an optional preventive modification that 
extends certain repetitive intervals. This proposed AD results from 
reports of cracks in the fuselage skin at the corners of the doorjamb 
for the main cabin cargo door. We are proposing this AD to detect and 
correct fatigue cracks in the fuselage skin, which could result in 
rapid decompression of the airplane.

DATES: We must receive comments on this proposed AD by October 31, 
2005.

ADDRESSES: Use one of the following addresses to submit comments on 
this proposed AD.
     DOT Docket Web site: Go to https://dms.dot.gov and follow 
the instructions for sending your comments electronically.
     Government-Wide Rulemaking Web Site: Go to https://
www.regulations.gov and follow the instructions for sending your 
comments electronically.
     Mail: Docket Management Facility, U.S. Department of 
Transportation, 400 Seventh Street SW., Nassif Building, room PL-401, 
Washington, DC 20590.
     Fax: (202) 493-2251.
     Hand Delivery: Room PL-401 on the plaza level of the 
Nassif Building, 400 Seventh Street SW., Washington, DC, between 9 a.m. 
and 5 p.m., Monday through Friday, except Federal holidays.
    Contact Boeing Commercial Airplanes, Long Beach Division, 3855 
Lakewood Boulevard, Long Beach, California 90846, Attention: Data and 
Service Management, Dept. C1-L5A (D800-0024), for the service 
information identified in this proposed 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:

Comments Invited

    We invite you to submit any relevant written data, views, or 
arguments regarding this proposed AD. Send your comments to an address 
listed in the ADDRESSES section. Include the docket number ``FAA-2005-
22425; Directorate Identifier 2005-NM-066-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of the proposed AD. We will 
consider all comments received by the closing date and may amend the 
proposed AD in light of those comments.
    We will post all comments we receive, without change, to https://
dms.dot.gov, including any personal information you provide. We will 
also post a report summarizing each substantive verbal contact with FAA

[[Page 54675]]

personnel concerning this proposed AD. Using the search function of 
that web site, anyone can find and read the comments in any of our 
dockets, including the name of the individual who sent the comment (or 
signed the comment on behalf of an association, business, labor union, 
etc.). You may review DOT's complete Privacy Act Statement in the 
Federal Register published on April 11, 2000 (65 FR 19477-78), or you 
may visit https://dms.dot.gov.

Examining the Docket

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

Discussion

    We have received reports of cracks in the fuselage skin at the 
corners of the doorjamb for the main cabin cargo door on McDonnell 
Douglas Model DC-8-71F airplanes. Cracks were found on airplanes that 
had accumulated 14,600 landings. The manufacturer's investigation 
showed that the cracks resulted from fatigue stress. Fatigue cracks, if 
not corrected, could progress and result in rapid decompression of the 
airplane.

Other Relevant Rulemaking

    On January 11, 1993, we issued AD 93-01-15, amendment 39-8469 (58 
FR 5576, January 22, 1993). We issued that AD to ensure the continuing 
structural integrity of McDonnell Douglas Model DC-8 airplanes. That AD 
requires revising the FAA-approved maintenance inspection program, 
which provides for inspection of the Principal Structural Elements 
(PSEs) identified in McDonnell Douglas Report No. L26-011, ``DC-8 
Supplemental Inspection Document (SID).'' That AD also requires 
reporting results of inspections to McDonnell Douglas, and repairing 
any cracked structure detected during the inspections.

Relevant Service Information

    We have reviewed Boeing Service Bulletin DC8-53-079, Revision 01, 
dated June 26, 2002. The service bulletin describes procedures for 
repetitive inspections for cracks of the doorjamb corners of the main 
cargo door. The inspections include radiographic, high frequency eddy 
current (HFEC), and visual (optically aided) inspections. Each 
inspection type is repeated in combination (e.g., radiographic and HFEC 
together) at varying intervals that range from 4,937 landings to 11,325 
landings depending on the type of inspection. These intervals are 
described in Table 1 of paragraph 1.E. ``Compliance'' of the service 
bulletin.
    If any crack is found that is 2.50 inches in length or less, the 
service bulletin describes procedures for repairing the fuselage skin 
and installing an external doubler. If any crack is found that is 
greater than 2.50 inches in length, the service bulletin specifies 
contacting the manufacturer for repair instructions and for reporting 
certain information. The service bulletin also gives procedures for a 
preventive modification of installing an external doubler at the corner 
of the main cabin cargo doorjamb.
    After any modification or repair, the service bulletin specifies 
that operators should inspect again for cracks of the modified or 
repaired doorjamb corner within 17,000 landings after doing the 
modification or repair, and then repeat the inspection at intervals not 
to exceed 4,400 landings.
    Accomplishing the actions specified in the service information is 
intended to adequately address the unsafe condition.
    The inspection program in Revision 01 of the service bulletin is an 
alternative method of compliance (AMOC) for the requirements of 
paragraphs (a) and (b) of AD 93-01-15 for the specified areas of PSE 
53.08.044.

FAA's Determination and Requirements of the Proposed AD

    We have evaluated all pertinent information and identified an 
unsafe condition that is likely to exist or develop on other airplanes 
of this same type design. For this reason, we are proposing this AD, 
which would require accomplishing the actions specified in the service 
information described previously, except as discussed under 
``Differences Between the Proposed AD and the Service Bulletin.''

Differences Between the Proposed AD and the Service Bulletin

    The service bulletin specifies to contact the manufacturer for 
instructions on how to repair certain conditions, but this proposed AD 
would require repairing those conditions in one of the following ways:
     Using a method that we approve; or
     Using data that meet the certification basis of the 
airplane, and that have been approved by an Authorized Representative 
for the Boeing Commercial Airplanes Delegation Option Authorization 
(DOA) Organization whom we have authorized to make those findings.
    Operators should note that, although the Accomplishment 
Instructions of the service bulletin describe procedures for submitting 
certain information to the manufacturer, this AD would not require that 
action.

Clarification of Inspection Language

    In this proposed AD, the ``visual (optically aided)'' inspection 
specified in the Boeing service bulletin is referred to as a ``detailed 
inspection.'' We have included the definition for a detailed inspection 
in a note in the proposed AD.

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 proposed AD.

                                                                     Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
                                       Work    Average labor                                                   Number of U.S.-
               Action                 hours    rate per hour          Parts            Cost per airplane     registered airplanes        Fleet cost
--------------------------------------------------------------------------------------------------------------------------------------------------------
Inspection, per inspection cycle...       20             $65  None.................  $1,300, per            166..................  $215,800, per
                                                                                      inspection cycle.                             inspection cycle.
Optional preventive modification          80              65  $26,881 to $30,913     $32,081 to $36,113...  Up to 166............  Up to between
 (per corner).                                                 (per corner,                                                         $5,325,446 and
                                                               depending on                                                         $5,994,758 (for one
                                                               airplane                                                             corner).
                                                               configuration).
--------------------------------------------------------------------------------------------------------------------------------------------------------


[[Page 54676]]

Authority for This Rulemaking

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

Regulatory Findings

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

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

The Proposed Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

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

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


Sec.  39.13  [Amended]

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

McDonnell Douglas: Docket No. FAA-2005-22425; Directorate Identifier 
2005-NM-066-AD.

Comments Due Date

    (a) The FAA must receive comments on this AD action by October 
31, 2005.

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 detailed, high frequency eddy current, and radiographic 
inspections, as applicable, for cracks of the doorjamb corners of 
the main cargo door in accordance with the Accomplishment 
Instructions of Boeing Service Bulletin DC8-53-079, Revision 01, 
dated June 26, 2002. Except as provided by paragraph (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.

    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.''

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 crack using a method approved in accordance 
with 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 Boeing Service Bulletin DC8-53-079, 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) 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

[[Page 54677]]

the certification basis of the airplane and 14 CFR 25.571, Amendment 
45, and the approval must specifically refer to this AD.
    (3) 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.

    Issued in Renton, Washington, on September 7, 2005.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 05-18401 Filed 9-15-05; 8:45 am]
BILLING CODE 4910-13-P
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