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, 14378-14381 [E8-5295]
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14378
Federal Register / Vol. 73, No. 53 / Tuesday, March 18, 2008 / Rules and Regulations
2008–06–19 Honeywell International Inc.
(formerly AlliedSignal Inc. and Garrett
Turbine Engine Co.): Amendment 39–
15431. Docket No. FAA–2007–29092;
Directorate Identifier 2007–NE–30–AD.
Effective Date
(a) This airworthiness directive (AD)
becomes effective April 22, 2008.
Affected ADs
Applicability
(c) This AD applies to Honeywell
International Inc. ATF3–6–4C, ATF3–6A–3C,
and ATF3–6A–4C turbofan engines equipped
with part number (P/N) 3002070–1 low
pressure compressor (LPC) Aft shaft. These
engines are installed on, but not limited to,
Dassault Aviation Fan Jet Falcon Series G
(Falcon 20G/HU25), and Dassault Aviation
Mystere-Falcon 200 airplanes.
Unsafe Condition
(d) This AD results from reports of eight
LPC aft shafts found cracked during
(b) None.
fluorescent penetrant inspection (FPI). We
are issuing this AD to prevent uncoupling
and overspeed of the low pressure turbine,
which could result in uncontained engine
failure and damage to the airplane.
Compliance
(e) You are responsible for having the
actions required by this AD performed within
the compliance times specified in Table 1
and Table 2 of this AD, unless the actions
have already been done.
TABLE 1.—ATF3–6A–4C TURBOFAN ENGINES, LPC AFT SHAFT REPLACEMENT COMPLIANCE SCHEDULE
For ATF3–6A–4C turbofan engines, if the
cycles-since-new (CSN) on the effective date of
this AD are:
Then replace the LPC Aft shaft:
(1)
(2)
(3)
(4)
Within
Within
Within
Within
6,500 or more CSN .......................................
5,000 to 6,499 CSN ......................................
4,000 to 4,999 CSN ......................................
Fewer than 4,000 CSN .................................
an
an
an
an
additional
additional
additional
additional
100 cycles-in-service (CIS).
800 CIS, but not more than 6,600 CSN, whichever occurs first.
1,500 CIS, but not more than 5,800 CSN, whichever occurs first.
2,000 CIS, but not more than 5,500 CSN, whichever occurs first.
TABLE 2.—ATF3–6–4C AND ATF3–6A–3C TURBOFAN ENGINES, LPC AFT SHAFT REPLACEMENT COMPLIANCE
SCHEDULE
For ATF3–6–4C and ATF3–6A–3C turbofan
engines, if the CSN on the effective date of this
AD are:
Then replace the LPC Aft shaft:
(1)
(2)
(3)
(4)
Within
Within
Within
Within
4,400 or more CSN .......................................
3,600 to 4,399 CSN ......................................
3,300 to 3,599 CSN ......................................
Fewer than 3,300 CSN .................................
additional
additional
additional
additional
100 CIS.
500 CIS, but not more than 4,500 CSN, whichever occurs first.
700 CIS, but not more than 4,100 CSN, whichever occurs first.
1,000 CIS, but not more than 4,000 CSN, whichever occurs first.
(f) Using the compliance schedule in Table
1 or Table 2 of this AD as applicable, remove
the LPC aft shaft, P/N 3002070–1, from
service, and install a serviceable LPC aft
shaft.
Issued in Burlington, Massachusetts, on
March 10, 2008.
Robert J. Ganley,
Acting Manager, Engine and Propeller
Directorate, Aircraft Certification Service.
[FR Doc. E8–5274 Filed 3–17–08; 8:45 am]
Definition
BILLING CODE 4910–13–P
(g) For the purpose of this AD, a
serviceable LPC aft shaft is an aft shaft with
a P/N not referenced in this AD.
DEPARTMENT OF TRANSPORTATION
Alternative Methods of Compliance
Federal Aviation Administration
(h) The Manager, Los Angeles Aircraft
Certification Office, has the authority to
approve alternative methods of compliance
for this AD if requested using the procedures
found in 14 CFR 39.19.
14 CFR Part 39
Related Information
rwilkins on PROD1PC63 with PROPOSALS
LPC Aft Shaft Replacement
an
an
an
an
RIN 2120–AA64
(i) Honeywell International Inc. Service
Bulletin No. ATF3–72–6240, Revision 1,
dated May 14, 2007, pertains to the subject
of this AD.
(j) Contact Joseph Costa, Aerospace
Engineer, Los Angeles Aircraft Certification
Office, FAA, Transport Airplane Directorate,
3960 Paramount Blvd., Lakewood CA 90712–
4137; e-mail: joseph.costa@faa.gov;
telephone: (562) 627–5246; fax: (562) 627–
5210, for more information about this AD.
Material Incorporated by Reference
(k) None.
VerDate Aug<31>2005
16:03 Mar 17, 2008
Jkt 214001
[Docket No. FAA–2007–0216; Directorate
Identifier 2007–NM–122–AD; Amendment
39–15435; AD 2008–06–23]
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
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
SUMMARY: The FAA is superseding an
existing airworthiness directive (AD)
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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 redefines 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
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Federal Register / Vol. 73, No. 53 / Tuesday, March 18, 2008 / Rules and Regulations
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 https://
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 onetime 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
14379
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 provided the public the
opportunity to participate in the
development of this AD. We have
considered the comment that was
received on the NPRM.
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.
Request To Give Credit for Prior
Submission of Inspection Findings
Costs of Compliance
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
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
Initial inspection for doubler installation .........................
Repetitive inspections (per inspection cycle) .................
Repair .............................................................................
2 to 4 .................................
2 to 8 .................................
164 to 184 .........................
$160 to $320 .....................
$160 to $640 .....................
$13,120 to $14,720 ...........
rwilkins on PROD1PC63 with PROPOSALS
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
VerDate Aug<31>2005
16:03 Mar 17, 2008
Jkt 214001
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.
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Fleet cost
$39,040 to $78,080.
$39,040 to $156,160.
$3,201,280 to $3,591,680.
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.
E:\FR\FM\18MRR1.SGM
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14380
Federal Register / Vol. 73, No. 53 / Tuesday, March 18, 2008 / Rules and Regulations
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
I
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
I
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The Federal Aviation
Administration (FAA) amends § 39.13
by removing amendment 39–14889 (72
FR 3044, January 24, 2007) and by
adding the following new airworthiness
directive (AD):
I
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.
rwilkins on PROD1PC63 with PROPOSALS
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
VerDate Aug<31>2005
16:03 Mar 17, 2008
Jkt 214001
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
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Fmt 4700
Sfmt 4700
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 lowfrequency 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
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Federal Register / Vol. 73, No. 53 / Tuesday, March 18, 2008 / Rules and Regulations
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.
rwilkins on PROD1PC63 with PROPOSALS
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,
VerDate Aug<31>2005
16:03 Mar 17, 2008
Jkt 214001
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: https://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
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 95
[Docket No. 30599; Amdt. No. 473]
IFR Altitudes; Miscellaneous
Amendments
Federal Aviation
Administration (FAA), DOT.
AGENCY:
ACTION:
Final rule.
SUMMARY: This amendment adopts
miscellaneous amendments to the
required IFR (instrument flight rules)
altitudes and changeover points for
certain Federal airways, jet routes, or
direct routes for which a minimum or
maximum en route authorized IFR
altitude is prescribed. This regulatory
action is needed because of changes
occurring in the National Airspace
System. These changes are designed to
provide for the safe and efficient use of
the navigable airspace under instrument
conditions in the affected areas.
Effective Date: 0901 UTC, April
10, 2008.
DATES:
FOR FURTHER INFORMATION CONTACT:
Donald P. Pate, Flight Procedure
Standards Branch (AMCAFS–420),
Flight Technologies and Programs
Division, Flight Standards Service,
Federal Aviation Administration, Mike
Monroney Aeronautical Center, 6500
South MacArthur Blvd., Oklahoma City,
OK 73169 (Mail Address: P.O. Box
25082, Oklahoma City, OK 73125)
telephone: (405) 954–4164.
This
amendment to part 95 of the Federal
Aviation Regulations (14 CFR part 95)
amends, suspends, or revokes IFR
altitudes governing the operation of all
aircraft in flight over a specified route
or any portion of that route, as well as
the changeover points (COPs) for
Federal airways, jet routes, or direct
routes as prescribed in part 95.
SUPPLEMENTARY INFORMATION:
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14381
The Rule
The specified IFR altitudes, when
used in conjunction with the prescribed
changeover points for those routes,
ensure navigation aid coverage that is
adequate for safe flight operations and
free of frequency interference. The
reasons and circumstances that create
the need for this amendment involve
matters of flight safety and operational
efficiency in the National Airspace
System, are related to published
aeronautical charts that are essential to
the user, and provide for the safe and
efficient use of the navigable airspace.
In addition, those various reasons or
circumstances require making this
amendment effective before the next
scheduled charting and publication date
of the flight information to assure its
timely availability to the user. The
effective date of this amendment reflects
those considerations. In view of the
close and immediate relationship
between these regulatory changes and
safety in air commerce, I find that notice
and public procedure before adopting
this amendment are impracticable and
contrary to the public interest and that
good cause exists for making the
amendment effective in less than 30
days.
Conclusion
The FAA has determined that this
regulation only involves an established
body of technical regulations for which
frequent and routine amendments are
necessary to keep them operationally
current. It, therefore—(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)
does not warrant preparation of a
regulatory evaluation as the anticipated
impact is so minimal. For the same
reason, the FAA certifies that this
amendment will not have a significant
economic impact on a substantial
number of small entities under the
criteria of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 95
Airspace, Navigation (air).
Issued in Washington, DC on March 11,
2008.
James J. Ballough,
Director, Flight Standards Service.
Adoption of the Amendment
Accordingly, pursuant to the authority
delegated to me by the Administrator,
part 95 of the Federal Aviation
Regulations (14 CFR part 95) is
amended as follows effective at 0901
UTC, April 10, 2008.
I
E:\FR\FM\18MRR1.SGM
18MRR1
]]>Agencies
[Federal Register Volume 73, Number 53 (Tuesday, March 18, 2008)]
[Rules and Regulations]
[Pages 14378-14381]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E8-5295]
-----------------------------------------------------------------------
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.
-----------------------------------------------------------------------
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 https://
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
----------------------------------------------------------------------------------------------------------------
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 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: https://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
