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


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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).

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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.
    <bullet> DOT Docket Web site: Go to http://dms.dot.gov and follow 
the instructions for sending your comments electronically.
    <bullet> Government-Wide Rulemaking Web Site: Go to http://www.regulations.gov and follow the instructions for sending your 
comments electronically.
    <bullet> Mail: Docket Management Facility, U.S. Department of 
Transportation, 400 Seventh Street SW., Nassif Building, room PL-401, 
Washington, DC 20590.
    <bullet> Fax: (202) 493-2251.
    <bullet> 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 http://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 http://dms.dot.gov.

Examining the Docket

    You may examine the AD docket on the Internet at http://dms.dot.gov, or in person at the Docket Management Facility office 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The Docket Management Facility office (telephone (800) 647-
5227) is located on the plaza level of the Nassif Building at the DOT 
street address stated in the ADDRESSES section. Comments will be 
available in the AD docket shortly after the Docket Management System 
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:
    <bullet> Using a method that we approve; or
    <bullet> 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
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                                       Work    Average labor                                                   Number of U.S.-
               Action                 hours    rate per hour          Parts            Cost per airplane     registered airplanes        Fleet cost
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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).
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[[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