[Federal Register: March 18, 2008 (Volume 73, Number 53)]
[Rules and Regulations]
[Page 14378-14381]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr18mr08-5]
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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;
Amendment 39-15435; AD 2008-06-23]
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: Final rule.
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SUMMARY: The FAA is superseding 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 new AD re-defines and more clearly describes the
optional actions for extending the repetitive inspection intervals.
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.
DATES: This AD becomes effective April 22, 2008.
The incorporation by reference of certain publications listed in
the AD was approved previously by the Director
[[Page 14379]]
of the Federal Register as of February 28, 2007 (72 FR 3044, January
24, 2007).
ADDRESSES: 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 AD, the regulatory evaluation,
any comments received, and other information. The address for the
Docket Office (telephone 800-647-5527) is the Document Management
Facility, U.S. Department of Transportation, Docket Operations, M-30,
West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590.
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:
Discussion
The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 to include an AD that supersedes AD 2007-02-02, amendment
39-14889 (72 FR 3044, January 24, 2007). The existing AD 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. That NPRM was published in the Federal Register on November
21, 2007 (72 FR 65471). That NPRM proposed to continue to require a
one-time inspection for previous repairs of the aft fuselage skin panel
at the longeron 28 skin splice, repetitive inspections for cracking of
the same area, and related investigative and corrective actions. That
NPRM also proposed to re-define and more clearly describe the optional
actions for extending the repetitive inspection intervals.
Comments
We provided the public the opportunity to participate in the
development of this AD. We have considered the comment that was
received on the NPRM.
Request To Give Credit for Prior Submission of Inspection Findings
UPS agrees with the intent of the NPRM. UPS requests, however, that
we revise paragraphs (k)(1) and (k)(2) of the NPRM to specify
submitting positive findings ``unless previously submitted to Boeing
for compliance with AD 2007-02-02.'' UPS asserts that this would allow
all alternative methods of compliance (AMOCs) that apply to AD 2007-02-
02 to be applicable to this new AD ``as per paragraph (k)(4) [sic].''
UPS states that this will prevent operators from having to submit data
already submitted previously for AD 2007-02-02, and again requesting
AMOC approval.
We do not agree with this request. Operators are always given
credit for work previously performed according to the existing AD by
means of the phrase in the compliance paragraph of this AD that states,
``Required * * * unless the actions have already been done.'' In
addition, paragraph (l)(4) of this AD (rather than paragraph (k)(4) as
specified by the commenter) states that AMOCs approved for compliance
with AD 2007-02-02 are acceptable for compliance with the corresponding
provisions of this AD. For these reasons, no change is needed to the AD
in this regard.
Conclusion
We have carefully reviewed the available data, including the
comment that has been received, and determined that air safety and the
public interest require adopting the AD as proposed.
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
are affected by this AD. The average labor rate is $80 per work hour.
This AD adds 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
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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 AD will not have federalism
implications under Executive Order 13132. This AD will 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 this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866;
(2) Is not a ``significant rule'' under 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 AD and placed it in the AD docket. See the ADDRESSES
section for a location to examine the regulatory evaluation.
[[Page 14380]]
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
0
Accordingly, under the authority delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
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]
0
2. The Federal Aviation Administration (FAA) amends Sec. 39.13 by
removing amendment 39-14889 (72 FR 3044, January 24, 2007) and by
adding the following new airworthiness directive (AD):
2008-06-23 McDonnell Douglas: Amendment 39-15435. Docket No. FAA-
2007-0216; Directorate Identifier 2007-NM-122-AD.
Effective Date
(a) This AD becomes effective April 22, 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
[[Page 14381]]
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 (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,
are approved as AMOCs for the corresponding provisions of this AD.
Material Incorporated by Reference
(m) You must use Boeing Alert Service Bulletin DC8-53A080, dated
June 22, 2004; and 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; as applicable, to perform the actions that
are required by this AD, unless the AD specifies otherwise.
(1) On February 28, 2007 (72 FR 3044, January 24, 2007), the
Director of the Federal Register approved the incorporation by
reference of these documents.
(2) 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 a copy of
this service information. You may review copies at the FAA,
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton,
Washington; or at the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-
register/cfr/ibr-locations.html.
Issued in Renton, Washington, on March 9, 2008.
Stephen P. Boyd,
Assistant Manager, Transport Airplane Directorate, Aircraft
Certification Service.
[FR Doc. E8-5295 Filed 3-17-08; 8:45 am]
BILLING CODE 4910-13-P