[Federal Register Volume 72, Number 65 (Thursday, April 5, 2007)]
[Proposed Rules]
[Pages 16744-16747]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: E7-6338]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-27777; Directorate Identifier 2006-NM-265-AD]
RIN 2120-AA64


Airworthiness Directives; McDonnell Douglas Model DC-8-53, DC-8-
55, DC-8F-54, and DC-8F-55 Airplanes; and Model DC-8-60, DC-8-60F, DC-
8-70, and DC-8-70F Series 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 McDonnell Douglas airplanes, identified above. This 
proposed AD would require a one-time inspection to determine the 
configuration of the airplane (tee or angle doubler installed on the 
left and right side of the flat aft pressure bulkhead from Longeron 9 
to Longeron 13). This proposed AD would also require repetitive 
inspections for cracking of the tee or angle doubler, and corrective 
actions if necessary. This proposed AD results from a report indicating 
that numerous operators have found cracks on the tee. We are proposing 
this AD to detect and correct stress corrosion cracking of the tee or 
angle doubler installed on the flat aft pressure bulkhead. Cracking in 
this area could continue to progress and damage the adjacent structure, 
which could result in loss of structural integrity of the airplane.

DATES: We must receive comments on this proposed AD by May 21, 2007.

ADDRESSES: Use one of the following addresses to submit comments on 
this proposed AD.
     DOT Docket Web site: Go to http://dms.dot.gov and follow 
the instructions for sending your comments electronically.
     Government-wide rulemaking Web site: Go to http://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 9:00 
a.m. and 5:00 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-2007-
27777; Directorate Identifier 2006-NM-265-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 
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

[[Page 16745]]

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 9:00 a.m. and 5:00 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 a report indicating that numerous operators have 
found cracks on the flat aft pressure bulkhead tee. The tee is 
installed on the left and right side of McDonnell Douglas Model DC-8 
airplanes that have a flat aft pressure bulkhead. The cracks, which 
originate in the corner radius of the tee from Longeron 9 to Longeron 
13, are a result of stress corrosion. This condition, if not corrected, 
could result in cracks continuing to progress, and consequent damage 
the adjacent structure and loss of structural integrity of the 
airplane.

Relevant Service Information

    We have reviewed Boeing Alert Service Bulletin DC8-53A081, dated 
November 14, 2006. The service bulletin describes procedures for doing 
an initial inspection using one of the following methods as applicable:
     For airplanes not previously repaired (Configuration 1), 
the service bulletin specifies doing the initial inspection for 
cracking of the tee installed on the left and right side of the flat 
aft pressure bulkhead from Longeron 9 to Longeron 13, according to one 
of three inspection methods specified in the DC-8 Supplemental 
Inspection Document (SID) L26-011, Volume II, 53-10-18: Methods 01A 
(High Frequency Eddy Current (HFEC)) and 01B (Ultrasonic) together; or 
Method 02 (HFEC); or Method 03 (Visual Aided).
     For airplanes previously repaired with an angle doubler 
that was installed in accordance with DC-8 Structural Repair Manual 53-
2-5, Figure 9 (Configuration 2), the service bulletin specifies an 
initial HFEC inspection for cracking of the angle doubler.
     For airplanes previously repaired with any repair other 
than one installed in accordance with DC-8 Structural Repair Manual 53-
2-5, Figure 9 (Configuration 3), the service bulletin specifies 
contacting Boeing for instructions.
    The service bulletin specifies the following actions, depending on 
crack findings:
     If no crack is found, the service bulletin specifies 
repeating the applicable inspection. For Configuration 1 airplanes, the 
repetitive intervals depend on the inspection type chosen, and range 
from within 2 years after the previous SID inspection or 600 flight 
cycles, whichever occurs earlier; to within 8 years after the previous 
SID inspection or 17,400 flight cycles, whichever occurs earlier. For 
Configuration 2 airplanes, the repetitive interval is 4,500 flight 
cycles.
     If any crack is found, the service bulletin specifies the 
corrective action of repairing the crack before further flight. The 
repair involves installing an angle doubler (if not previously 
installed) or removing the cracked angle doubler and installing a new 
one (if previously installed). The service bulletin states that the 
repetitive interval after repair is 4,500 flight cycles, and only the 
HFEC inspection type is specified for the repetitive inspections.
    The service bulletin also specifies that, for Configuration 1 
airplanes, if maintenance records show that the flat aft pressure 
bulkhead tee was previously inspected using one of the three inspection 
methods specified in the DC-8 SID L26-011, Volume II, 53-10-18, and no 
crack was found, the inspections may be continued at the applicable 
repetitive interval specified for Configuration 1 airplanes on which no 
crack is found during the initial inspection.
    Accomplishing the actions specified in the service information is 
intended to adequately address the unsafe condition.

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 
``Difference between the Proposed AD and the Service Bulletin.'' This 
proposed AD also would require determining the configuration of the 
airplane.

Difference 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 
Organization whom we have authorized to make those findings.

Costs of Compliance

    There are about 321 airplanes of the affected design in the 
worldwide fleet. This proposed AD would affect about 139 airplanes of 
U.S. registry. The following table provides the estimated costs for 
U.S. operators to comply with this proposed AD. The average labor rate 
is $80 per work hour.

                                                 Estimated Costs
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                                                       Cost per
              Action                  Work hours       airplane           Fleet cost
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Inspection to determine the                      1             $80  $11,120.
 configuration of the airplane,
 and to determine previous
 inspection method.
Configuration 1, per inspection                 11       $880, per  Up to $122,320, per
 cycle.                                                 inspection   inspection cycle.
                                                             cycle

[[Page 16746]]

 
Configuration 2, per inspection                  5       $400, per  Up to $55,600, per
 cycle.                                                 inspection   inspection cycle.
                                                             cycle
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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-2007-27777; Directorate Identifier 
2006-NM-265-AD.

Comments Due Date

    (a) The FAA must receive comments on this AD action by May 21, 
2007.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to McDonnell Douglas Model DC-8-53, DC-8-55, 
DC-8-61, DC-8-61F, DC-8-62, DC-8-62F, DC-8-63, DC-8-63F, DC-8-71, 
DC-8-71F, DC-8-72, DC-8-72F, DC-8-73, DC-8-73F, DC-8F-54, and DC-8F-
55 airplanes, certificated in any category; as identified in Boeing 
Alert Service Bulletin DC8-53A081, dated November 14, 2006.

Unsafe Condition

    (d) This AD results from a report indicating that numerous 
operators have found cracks on the tee installed on the left and 
right side of the flat aft pressure bulkhead from Longeron 9 to 
Longeron 13. We are issuing this AD to detect and correct stress 
corrosion cracking of the tee or angle doubler installed on the flat 
aft pressure bulkhead. Cracking in this area could continue to 
progress and damage the adjacent structure, which could result in 
loss of structural integrity 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 and Related Investigative/Corrective Actions

    (f) For all airplanes: Within 24 months after the effective date 
of this AD, inspect the left and right side of the flat aft pressure 
bulkhead from Longeron 9 to Longeron 13 to determine whether a tee 
is installed (also called Configuration 1 airplanes) or an angle is 
installed; and if any angle was installed in accordance with the DC-
8 Structural Repair Manual 52-2-5, Figure 9 (also called 
Configuration 2 airplanes), or in accordance with any other repair 
method (also called Configuration 3 airplanes). A review of airplane 
maintenance records is acceptable in lieu of this inspection if the 
applicable installation can be conclusively determined from that 
review.
    (1) For airplanes determined to be either Configuration 1 or 
Configuration 2: Within 24 months after the effective date of this 
AD, do the applicable inspection for cracking of the tee or angle 
doubler, and do all applicable corrective actions before further 
flight, by accomplishing all the actions specified in the 
Accomplishment Instructions of Boeing Alert Service Bulletin DC8-
53A081, dated November 14, 2006. Repeat the applicable inspection 
thereafter at the applicable interval specified in Paragraph 1.E, 
``Compliance,'' of Boeing Alert Service Bulletin DC8-53A081, dated 
November 14, 2006.
    (2) For airplanes determined to be Configuration 1 airplanes: A 
review of the airplane maintenance records to determine if the tee 
was previously inspected using one of the three inspection methods 
specified in the DC-8 Supplemental Inspection Document (SID) L26-
011, Volume II, 53-10-18; and to determine that no crack was found; 
is acceptable to determine the type of inspection and corresponding 
repetitive interval if the inspection type and crack finding can be 
conclusively determined from that review.
    (3) For airplanes determined to be Configuration 3 airplanes: 
Within 24 months after the effective date of this AD, repair the 
previous installation. Where Boeing Alert Service Bulletin DC8-
53A081, dated November 14, 2006, specifies to contact Boeing for 
instructions, repair using a method approved in accordance with the 
procedures specified in paragraph (g) of this AD.

Alternative Methods of Compliance (AMOCs)

    (g)(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.

[[Page 16747]]

    (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.

    Issued in Renton, Washington, on March 29, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
 [FR Doc. E7-6338 Filed 4-4-07; 8:45 am]
BILLING CODE 4910-13-P