[Federal Register: November 21, 2007 (Volume 72, Number 224)]
[Proposed Rules]
[Page 65471-65474]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr21no07-16]
=======================================================================
-----------------------------------------------------------------------
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).
-----------------------------------------------------------------------
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
------------------------------------------------------------------------
Corresponding requirement
Requirement in AD 2007-02-02 in this proposed AD
------------------------------------------------------------------------
paragraph (a)............................. paragraph (f).
paragraph (b)............................. paragraph (g).
paragraph (c)............................. paragraph (h).
------------------------------------------------------------------------
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
----------------------------------------------------------------------------------------------------------------
Action Work hours Cost per airplane Fleet cost
----------------------------------------------------------------------------------------------------------------
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.
----------------------------------------------------------------------------------------------------------------
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