[Federal Register Volume 72, Number 224 (Wednesday, November 21, 2007)]
[Proposed Rules]
[Pages 65471-65474]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: E7-22725]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-0216; Directorate Identifier 2007-NM-122-AD]
RIN 2120-AA64


Airworthiness Directives; McDonnell Douglas Model DC-8-55, DC-8F-
54, and DC-8F-55 Airplanes; and Model DC-8-60, DC-8-70, DC-8-60F, 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 supersede an existing airworthiness 
directive (AD) that applies to certain McDonnell Douglas Model DC-8-55, 
DC-8F-54, and DC-8F-55 airplanes; and Model DC-8-60, DC-8-70, DC-8-60F, 
and DC-8-70F series airplanes. The existing AD currently requires a 
one-time inspection for previous repairs of the aft fuselage skin panel 
at the longeron 28 skin splice; repetitive inspections for cracks of 
the same area; and related investigative and corrective actions. The 
existing AD also provides optional actions for extending the repetitive 
inspection intervals. This proposed AD would re-define and more clearly 
describe the optional actions for extending the repetitive inspection 
intervals. This proposed AD results from our determination that the 
inspections and actions described in the existing AD do not adequately 
address the unsafe condition. We are proposing this AD to detect and 
correct cracks in the aft fuselage skin at the longeron 28 skin splice, 
which could lead to loss of structural integrity of the aft fuselage, 
resulting in rapid decompression of the airplane.

DATES: We must receive comments on this proposed AD by January 7, 2008.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue, SE., Washington, DC 20590.
     Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays.
    For service information identified in this AD, contact Boeing 
Commercial Airplanes, Long Beach Division, 3855 Lakewood Boulevard, 
Long Beach, California 90846, Attention: Data and Service Management, 
Dept. C1-L5A (D800-0024).

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov; or in person at the Docket Management Facility 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The AD docket contains this proposed AD, the regulatory 
evaluation, any comments received, and other information. The street 
address for the Docket Office (telephone 800-647-5527) is in the 
ADDRESSES section. Comments will be available in the AD docket shortly 
after receipt.

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: 

[[Page 65472]]

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-
0216; Directorate Identifier 2007-NM-122-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://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    On January 5, 2007, we issued AD 2007-02-02, amendment 39-14889 (72 
FR 3044, January 24, 2007), for certain McDonnell Douglas Model DC-8-
55, DC-8F-54, and DC-8F-55 airplanes; and Model DC-8-60, DC-8-70, DC-8-
60F, and DC-8-70F series airplanes. That AD requires a one-time 
inspection for previous repairs of the aft fuselage skin panel at the 
longeron 28 skin splice; repetitive inspections for cracks of the same 
area; related investigative and corrective actions; and reporting 
inspection findings to the manufacturer. That AD also provides optional 
actions for extending the repetitive inspection intervals. That AD 
resulted from a report indicating that a crack has been found in the 
aft fuselage skin at the longeron 28 skin splice. We issued that AD to 
detect and correct cracks in the aft fuselage skin at the longeron 28 
skin splice, which could lead to loss of structural integrity of the 
aft fuselage, resulting in rapid decompression of the airplane.

Actions Since Existing AD Was Issued

    Since we issued AD 2007-02-02, we have determined that the 
inspections and optional modification/repair described in that AD do 
not adequately address the unsafe condition. We concluded that more 
careful inspection of areas already repaired and reinforced by the 
installation of doublers was needed. Accordingly, we propose to re-
define and more clearly describe certain inspections and the optional 
modification/repair to completely address the unsafe condition 
described in that AD.

FAA's Determination and Requirements of the Proposed AD

    We have evaluated all pertinent information and identified an 
unsafe condition that is likely to develop on other airplanes of the 
same type design. For this reason, we are proposing this AD, which 
would supersede AD 2007-02-02, re-define the requirements of that AD, 
and clarify the optional modification/repair described in that AD 
which, if done, would allow extending the repetitive inspection 
intervals.

Changes to Existing AD

    This proposed AD would re-define certain requirements and clarify 
the optional modification/repair of AD 2007-02-02. Since AD 2007-02-02 
was issued, the AD format has been revised, and certain paragraphs have 
been rearranged. As a result, the corresponding paragraph identifiers 
have changed in this proposed AD, as listed in the following table:

                      Revised Paragraph Identifiers
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                                             Corresponding  requirement
       Requirement in AD 2007-02-02             in this  proposed AD
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paragraph (a).............................  paragraph (f).
paragraph (b).............................  paragraph (g).
paragraph (c).............................  paragraph (h).
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Costs of Compliance

    There are approximately 508 airplanes of the affected design in the 
worldwide fleet. The FAA estimates that 244 airplanes of U.S. registry 
would be affected by this proposed AD. The average labor rate is $80 
per work hour. This proposed AD would add no additional costs; however, 
we are repeating the costs from AD 2007-02-02 for the convenience of 
affected operators.

                                                 Estimated Costs
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              Action                           Work hours               Cost per airplane        Fleet cost
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Initial Inspection for doubler     2 to 4...........................  $160 to $320........  $39,040 to $78,080.
 installation.
Repetitive Inspections (per        2 to 8...........................  $160 to $640........  $39,040 to $156,160.
 inspection cycle).
Repair...........................  164 to 184.......................  $13,120 to $14,720..  $3,201,280 to
                                                                                             $3,591,680.
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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.

[[Page 65473]]

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 
removing amendment 39-14889 (72 FR 3044, January 24, 2007) and adding 
the following new airworthiness directive (AD):

McDonnell Douglas: Docket No. FAA-2007-0216; Directorate Identifier 
2007-NM-122-AD.

Comments Due Date

    (a) The FAA must receive comments on this AD action by January 
7, 2008.

Affected ADs

    (b) This AD supersedes AD 2007-02-02.

Applicability

    (c) This AD applies to McDonnell Douglas Model DC-8-55, DC-8F-
54, DC-8F-55, DC-8-61, DC-8-62, DC-8-63, DC-8-61F, DC-8-62F, DC-8-
63F, DC-8-71, DC-8-72, DC-8-73, DC-8-71F, DC-8-72F, and DC-8-73F 
airplanes, certificated in any category; as identified in Boeing 
Alert Service Bulletin DC8-53A080, dated June 22, 2004.

Unsafe Condition

    (d) This AD results from our determination that the inspections 
and actions described in the existing AD do not adequately address 
the unsafe condition. We are issuing this AD to detect and correct 
cracks in the aft fuselage skin at the longeron 28 skin splice, 
which could lead to loss of structural integrity of the aft 
fuselage, resulting 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.

Requirements of AD 2007-02-02

One-Time Inspection for Previous Repairs

    (f) For all airplanes: At the applicable time in paragraph 
(f)(1) or (f)(2) of this AD, do a general visual inspection to 
determine if there are previous repairs of the aft fuselage skin 
panel at the longeron 28 skin splice; in accordance with the 
Accomplishment Instructions of Boeing Alert Service Bulletin DC8-
53A080, dated June 22, 2004. Then do the applicable actions 
specified in paragraphs (g) and (h) of this AD.
    (1) For airplanes that have accumulated fewer than 24,000 total 
flight cycles as of February 28, 2007 (the effective date of AD 
2007-02-02): Within 24 months after February 28, 2007, or prior to 
accumulating 24,000 total flight cycles, whichever occurs later.
    (2) For airplanes that have accumulated 24,000 total flight 
cycles or more as of February 28, 2007: Within 12 months after 
February 28, 2007.

    Note 1: For the purposes of this AD, a general visual inspection 
is: ``A visual examination of an interior or exterior area, 
installation, or assembly to detect obvious damage, failure, or 
irregularity. This level of inspection is made from within touching 
distance unless otherwise specified. A mirror may be necessary to 
ensure visual access to all surfaces in the inspection area. This 
level of inspection is made under normally available lighting 
conditions such as daylight, hangar lighting, flashlight, or 
droplight and may require removal or opening of access panels or 
doors. Stands, ladders, or platforms may be required to gain 
proximity to the area being checked.''

Repetitive Inspections for Areas That Do Not Have a Previous Repair

    (g) For areas that do not have a previous repair: Before further 
flight after the initial inspection in paragraph (f) of this AD, do 
general visual and high-frequency eddy current (HFEC) inspections 
for discrepancies at longeron 28 between the bolted connection of 
the tail section to forward of the flat aft pressure bulkhead, on 
both the left and right sides, and do all applicable related 
investigative and corrective actions before further flight. Do all 
actions in accordance with the Accomplishment Instructions of Boeing 
Alert Service Bulletin DC8-53A080, dated June 22, 2004. Repeat the 
general visual and HFEC inspections thereafter at intervals not to 
exceed 2,000 flight cycles until an optional action in paragraph (i) 
of this AD is accomplished.

Repetitive Inspections and Repair for Areas That Have a Previous 
Repair

    (h) For areas that have a previous repair: Within 24 months 
after accomplishing the initial inspection in paragraph (f) of this 
AD, remove the previous repair(s), and install a local repair, in 
accordance with Boeing DC-8 Service Rework Drawing SR08530032, dated 
January 13, 2004, including Boeing Parts List PL SR08530032, dated 
January 7, 2004, Boeing Advance Engineering Order, Advanced Drawing 
Change A, dated April 1, 2004, and Boeing Engineering Order, dated 
January 13, 2004. Do the inspections in paragraph (j) of this AD 
thereafter at the applicable interval specified in paragraph (j)(1) 
or (j)(2) of this AD.

New Requirements of This AD

Optional Modification/Repair

    (i) Installing a full-length preventive modification, doing a 
full-length repair, or doing a local repair, in accordance with 
Boeing DC-8 Service Rework Drawing SR08530032, dated January 13, 
2004, including Boeing Parts List PL SR08530032, dated January 7, 
2004, Boeing Advance Engineering Order, Advanced Drawing Change A, 
dated April 1, 2004, and Boeing Engineering Order, dated January 13, 
2004, ends the repetitive inspection intervals specified in 
paragraph (g) of this AD.

Extended Repetitive Inspection Intervals

    (j) After removing the previous repair(s) and doing the actions 
specified in paragraph (h) of this AD or doing any optional repair 
or modification described in paragraph (i) of this AD: Do the 
actions described in paragraph (j)(1) or (j)(2) of this AD as 
applicable, in accordance with the Accomplishment Instructions of 
Boeing Alert Service Bulletin DC8-53A080, dated June 22, 2004. If 
any discrepancy is discovered during any inspection required by this 
paragraph, before further flight, repair the discrepancy using a 
method approved in accordance with the procedures specified in 
paragraph (l) of this AD.
    (1) For areas that have been repaired on airplanes that do have 
internal finger doublers installed: Within 30,000 flight cycles 
after doing the optional repair or modification, do a general visual 
inspection for discrepancies along all four external edges of the 
doublers. Repeat the inspection thereafter at intervals not to 
exceed 5,000 flight cycles.
    (2) For areas that have been repaired on airplanes that do not 
have internal finger doublers installed: Do the actions specified in 
paragraph (j)(2)(i) or (j)(2)(ii) of this AD, as applicable.
    (i) For any repair that is 12 inches or less along the longeron: 
Within 15,000 flight cycles after removing the previous repair(s) 
and doing the actions specified in paragraph (h) of this AD or doing 
any optional repair or modification specified in paragraph (i) of 
this AD, do a general visual inspection for discrepancies along all 
four external edges of the doublers. Repeat the general visual 
inspection thereafter at intervals not to exceed 5,000 flight 
cycles.
    (ii) For any repair that is greater than 12 inches in length 
along the longeron: Within 15,000 flight cycles after removing the 
previous repair(s) and doing the actions specified in paragraph (h) 
of this AD or doing any optional repair or modification specified in 
paragraph (i) of this AD, do a low-frequency eddy current (LFEC) 
inspection for discrepancies along all four external edges of the 
doublers. Repeat the LFEC inspection thereafter at intervals not to 
exceed 10,000 flight cycles.

Reporting of Results

    (k) Submit a report of positive findings of the inspections 
required by paragraphs (g) and (j) of this AD to Boeing Commercial 
Airplanes, Manager, Structure/Payloads, Technical and Fleet Support, 
Service Engineering/Commercial Aviation Services, Long Beach 
Division, 3855 Lakewood Boulevard, Long Beach, California 90846, at 
the applicable time specified in paragraph (k)(1) or (k)(2) of this 
AD. The report must include the inspection results, a description of 
any discrepancies found, the airplane fuselage number, and the total 
number of landings and flight hours on the airplane. Information 
collection requirements

[[Page 65474]]

contained in this AD have been approved by the Office of Management 
and Budget (OMB) under the provisions of the Paperwork Reduction Act 
(44 U.S.C. 3501 et seq.) and have been assigned OMB Control Number 
2120-0056.
    (1) For any inspection accomplished after the effective date of 
this AD: Submit the report within 30 days after performing the 
inspection.
    (2) For any inspection accomplished prior to the effective date 
of this AD: Submit the report within 30 days after the effective 
date of this AD.

Alternative Methods of Compliance (AMOCs)

    (l)(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) To request a different method of compliance or a different 
compliance time for this AD, follow the procedures in 14 CFR 39.19. 
Before using any approved AMOC on any airplane to which the AMOC 
applies, notify your appropriate principal inspector (PI) in the FAA 
Flight Standards District Office (FSDO), or lacking a PI, your local 
FSDO.
    (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) AMOCs approved previously in accordance with AD 2007-02-02, 
amendment 39-14889, are approved as AMOCs for the corresponding 
provisions of this AD.

    Issued in Renton, Washington, on November 13, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
 [FR Doc. E7-22725 Filed 11-20-07; 8:45 am]
BILLING CODE 4910-13-P