[Federal Register: October 8, 2003 (Volume 68, Number 195)]
[Proposed Rules]
[Page 58044-58045]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr08oc03-15]
[[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: 9-anm-nprmcomment@faa.gov. 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