[Federal Register Volume 68, Number 195 (Wednesday, October 8, 2003)]
[Proposed Rules]
[Pages 58044-58045]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 03-25492]



[[Page 58044]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-NM-183-AD]
RIN 2120-AA64


Airworthiness Directives; McDonnell Douglas DC-8-11, DC-8-12, DC-
8-21, DC-8-31, DC-8-32, DC-8-33, DC-8-41, DC-8-42, and DC-8-43 
Airplanes; DC-8-50 Series Airplanes; DC-8F-54 and DC-8F-55 Airplanes; 
DC-8-60 Series Airplanes; DC-8-60F Series Airplanes; DC-8-70 Series 
Airplanes; and DC-8-70F Series Airplanes; All with Flat Aft Pressure 
Bulkheads

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: This document proposes the adoption of a new airworthiness 
directive (AD) that is applicable to certain McDonnell Douglas Model 
DC-8 airplanes. This proposal would require a one-time inspection of 
the aft fuselage skin panel at the longeron 28 skin splice for cracks; 
repair of any cracks detected; and reporting of the findings of the 
inspection to the manufacturer. This action is necessary 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. This action is 
intended to address the identified unsafe condition.

DATES: Comments must be received by November 24, 2003.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 2001-NM-183-AD, 1601 Lind Avenue, SW., 
Renton, Washington 98055-4056. Comments may be inspected at this 
location between 9 a.m. and 3 p.m., Monday through Friday, except 
Federal holidays. Comments may be submitted via fax to (425) 227-1232. 
Comments may also be sent via the Internet using the following address: 
[email protected]. Comments sent via fax or the Internet must 
contain ``Docket No. 2001-NM-183-AD'' in the subject line and need not 
be submitted in triplicate. Comments sent via the Internet as attached 
electronic files must be formatted in Microsoft Word 97 for Windows or 
ASCII text.

FOR FURTHER INFORMATION CONTACT: Jon Mowery, Aeronautical 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

    Interested persons are invited to participate in the making of the 
proposed rule by submitting such written data, views, or arguments as 
they may desire. Communications shall identify the Rules Docket number 
and be submitted in triplicate to the address specified above. All 
communications received on or before the closing date for comments, 
specified above, will be considered before taking action on the 
proposed rule. The proposals contained in this action may be changed in 
light of the comments received.
    Submit comments using the following format:
    [sbull] Organize comments issue-by-issue. For example, discuss a 
request to change the compliance time and a request to change the 
service bulletin reference as two separate issues.
    [sbull] For each issue, state what specific change to the proposed 
AD is being requested.
    [sbull] Include justification (e.g., reasons or data) for each 
request.
    Comments are specifically invited on the overall regulatory, 
economic, environmental, and energy aspects of the proposed rule. All 
comments submitted will be available, both before and after the closing 
date for comments, in the Rules Docket for examination by interested 
persons. A report summarizing each FAA-public contact concerned with 
the substance of this proposal will be filed in the Rules Docket.
    Commenters wishing the FAA to acknowledge receipt of their comments 
submitted in response to this action must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket Number 2001-NM-183-AD.'' The postcard will be date stamped 
and returned to the commenter.

Availability of NPRMs

    Any person may obtain a copy of this NPRM by submitting a request 
to the FAA, Transport Airplane Directorate, ANM-114, Attention: Rules 
Docket No. 2001-NM-183-AD, 1601 Lind Avenue, SW., Renton, Washington 
98055-4056.

Discussion

    The FAA has received a report indicating that a crack has been 
found in the aft fuselage skin at the longeron 28 skin splice. This 
crack was found just forward of the aft pressure bulkhead on a 
McDonnell Douglas Model DC-8-71F airplane, between fuselage stations 
Y=1704 and Y=1717. Analysis indicated that the crack is due to fatigue 
and could be a result of multi-site damage. Failure to detect and 
correct such a crack before it grows to a critical length could lead to 
loss of structural integrity of the aft fuselage, resulting in rapid 
decompression of the airplane.
    The subject area on Model DC-8-71F airplanes is almost identical to 
that on the other Model DC-8 airplanes. Therefore, those Model DC-8 
airplanes may be subject to the unsafe condition revealed on the Model 
DC-8-71F airplanes.

Explanation of Relevant Service Information

    There is not yet any service information pertaining to the proposed 
inspection of the aft fuselage skin panel at the longeron 28 skin spice 
for cracks and the repair of any such cracks. The manufacturer is 
developing service information which may include repetitive inspections 
and repairs. However, several methods in the manufacturer's Non-
Destructive Testing Standard Practice Manual are referenced in this 
proposed AD as approved methods of inspection.

Explanation of Requirements of Proposed Rule

    Since an unsafe condition has been identified that is likely to 
exist or develop on other products of this same type design, the 
proposed AD would require performing a one-time inspection of the aft 
fuselage skin panel at the longeron 28 skin splice for cracks, 
repairing any cracks detected, and reporting results of the inspection 
(both negative and positive) to the manufacturer.

Interim Action

    This is considered to be interim action. The manufacturer has 
advised that it currently is developing a modification that will 
address the unsafe condition addressed by this AD. Once this 
modification is developed, approved, and available, the FAA may 
consider additional rulemaking.

Cost Impact

    There are approximately 264 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, that it would take approximately 
3 work hours per airplane to accomplish the proposed inspection and 
reporting of results, and that the average labor rate is $65 per

[[Page 58045]]

work hour. Based on these figures, the cost impact of the proposed 
actions on U.S. operators is estimated to be $47,580, or $195 per 
airplane.
    The cost impact figure discussed above is based on assumptions that 
no operator has yet accomplished any of the proposed requirements of 
this AD action, and that no operator would accomplish those actions in 
the future if this proposed AD were not adopted. The cost impact 
figures discussed in AD rulemaking actions represent only the time 
necessary to perform the specific actions actually required by the AD. 
These figures typically do not include incidental costs, such as the 
time required to gain access and close up, planning time, or time 
necessitated by other administrative actions.

Regulatory Impact

    The regulations proposed herein 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. Therefore, it 
is determined that this proposal would not have federalism implications 
under Executive Order 13132.
    For the reasons discussed above, I certify that this 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) if promulgated, 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. A copy of the draft 
regulatory evaluation prepared for this action is contained in the 
Rules Docket. A copy of it may be obtained by contacting the Rules 
Docket at the location provided under the caption ADDRESSES.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

The Proposed Amendment

    Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration proposes to amend 
part 39 of the Federal Aviation Regulations (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. Section 39.13 is amended by adding the following new 
airworthiness directive:

McDonnell Douglas: Docket 2001-NM-183-AD.

    Applicability: McDonnell Douglas Model DC-8-11, DC-8-12, DC-8-
21, DC-8-31, DC-8-32, DC-8-33, DC-8-41, DC-8-42, and DC-8-43 
airplanes; DC-8-51, DC-8-52, DC8-53, and DC-8-55 airplanes; DC-8F-54 
and DC-8F-55 airplanes; DC-8-61, DC-8-62, and DC-8-63 airplanes; DC-
8-61F, DC-8-62F, and DC-8-63F airplanes; DC-8-71, DC-8-72, and DC-8-
73 airplanes; and DC-8-71F, DC-8-72F, and DC-8-73F airplanes; all 
with flat aft pressure bulkheads; certificated in any category.
    Compliance: Required as indicated, unless accomplished 
previously.
    To detect and correct cracks in the aft fuselage skin at the 
longeron 28 skin splice, which could result in loss of structural 
integrity of the aft fuselage, resulting in a rapid decompression of 
the airplane; accomplish the following:

One-time Inspection for Cracks

    (a) For airplanes that have accumulated fewer than 24,000 total 
flight cycles as of the effective date of this AD: Within 2 years 
after the effective date of this AD or prior to accumulating a total 
of 24,000 flight cycles, whichever occurs later, perform an 
inspection of the aft fuselage skin panel having part number (P/N) 
5649328-3 along the rivet row common to longeron 28 from the tail 
joint to the aft pressure bulkhead for cracks, using one of the 
methods indicated in paragraph (a)(1), (a)(2), or (a)(3) of this AD.
    (1) Non-Destructive Testing Standard Practice Manual MDC-
93K0393, 06-10-01.001, High Frequency Eddy Current, Procedure 1, 
scan 48, crack direction Y, calibration N.
    (2) Non-Destructive Testing Standard Practice Manual MDC-
93K0393, 06-10-03.001, Magnetic-optic/Eddy Current Imager, Procedure 
1.
    (3) A method approved by the Manager, Los Angeles Aircraft 
Certification Office (ACO), FAA.

    Note 1: The fuselage skin is 0.05 inch thick 7075-TA aluminum, 
and the fasteners are NAS 1097 DD \6/32\-inch diameter with control 
countersink.


    Note 2: The tail joint is at Station 1490 for DC-8-50 series 
airplanes, at Station 1530 for DC-8-62, DC-8-62F, DC-8-72, and DC-8-
72F airplanes, and at Station 1690 for DC-8-63, DC-8-63F, DC-8-71, 
and DC-8-73 airplanes.

    (b) For airplanes that have accumulated 24,000 total flight 
cycles or more as of the effective date of this AD: Within 1 year 
after the effective date of this AD or within 1,000 flight cycles 
after the effective date of this AD, whichever occurs first, perform 
the inspection required by paragraph (a) of this AD.
    (c) If no crack is detected during the one-time inspection 
required by paragraph (a) or (b) of this AD, as applicable: No 
further action is required by this AD, other than the reporting of 
the results of the inspection, as required by paragraph (e) of this 
AD.

Repair

    (d) If any cracks are detected during the one-time inspection 
required by paragraph (a) or (b) of this AD: Prior to further 
flight, repair the crack or cracks per a manner approved by the 
Manager, Los Angeles ACO, FAA.

Reporting of Results

    (e) Submit a report of findings (both positive and negative) of 
the inspection required by paragraph (a) or (b) of this AD to the 
Manager, Structure/Payloads, Technical and Fleet Support, Service 
Engineering/Commercial Aviation Services, Boeing Company at the 
applicable time specified in paragraph (e)(1) or (e)(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 contained in this AD have been approved by 
the Office of Management and Budget (OMB) under the provisions of 
the Paperwork Reduction Act of 1980 (44 U.S.C. 3501 et seq.) and 
have been assigned OMB Control Number 2120-0056.
    (1) For airplanes on which the one-time inspection is 
accomplished after the effective date of this AD: Submit the report 
within 10 days after performing the inspection.
    (2) For airplanes on which the one-time inspection was 
accomplished prior to the effective date of this AD: Submit the 
report within 10 days after the effective date of this AD.

Alternative Methods of Compliance

    (f)(1) In accordance with 14 CFR 39.19, the Manager, Los Angeles 
ACO, FAA, is authorized to approve alternative methods of compliance 
for this AD.
    (2) An AMOC that provides an acceptable level of safety may be 
used for repair of any cracks detected during the inspection 
required by paragraph (a) or (b) of this AD, if it is approved by a 
Boeing Company Designated Engineering Representative (DER) who has 
been authorized by the Manager, Los Angeles ACO, to make such 
findings.

    Note 3: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Los Angeles ACO.


    Issued in Renton, Washington, on October 2, 2003.
Ali Bahrami,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 03-25492 Filed 10-7-03; 8:45 am]
BILLING CODE 4910-13-P