Airworthiness Directives; McDonnell Douglas Corporation Model DC-10-10, DC-10-10F, and MD-10-10F Airplanes, 82333-82335 [2010-33001]
Download as PDF
Federal Register / Vol. 75, No. 250 / Thursday, December 30, 2010 / Proposed Rules
Alternative Methods of Compliance
(AMOCs)
(h)(1) The Manager, Atlanta Aircraft
Certification Office, FAA, has the authority to
approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19.
In accordance with 14 CFR 39.19, send your
request to your principal inspector or local
Flight Standards District Office, as
appropriate. If sending information directly
to the manager of the ACO, send it to the
attention of the person identified in the
Related Information section of this AD.
(2) Before using any approved AMOC,
notify your Principal Maintenance Inspector
or Principal Avionics Inspector, as
appropriate, or lacking a principal inspector,
your local Flight Standards District Office.
(3) AMOCs approved for AD 99–15–04 R1
are approved as AMOCs for this AD.
Related Information
(i) For more information about this AD,
contact Darby Mirocha, Aerospace Engineer,
FAA, Atlanta Aircraft Certification Office,
1701 Columbia Avenue, College Park,
Georgia 30337; phone: (404) 474–5573; fax:
(404) 474–5605; e-mail:
darby.mirocha@faa.gov.
(j) For service information identified in this
AD, contact Piper Aircraft, Inc., 2926 Piper
Drive, Vero Beach, Florida 32960; telephone:
(772) 567–4361; fax: (772) 978–6573;
Internet: https://www.piper.com/home/pages/
publications.cfm. You may review copies of
the referenced service information at the
FAA, Small Airplane Directorate, 901 Locust
St., Kansas City, MO 64106. For information
on the availability of this material at the
FAA, call (816) 329–4148.
Appendix 1 to Docket No. FAA–2010–1295
Model PA–46–310P (Mailbu)—Emergency
Procedures for the Pilot’s Operating
Handbook (POH)
(1) If the turbine inlet temperature
indication fails or is suspected of failure
during takeoff, climb, descent, or landing,
maintain FULL RICH mixture to assure
adequate fuel flow for engine cooling.
(2) If the turbine inlet temperature
indication fails or is suspected of failure after
cruise power has been set, maintain cruise
power setting and lean to 6 gallons per hour
(GPH) fuel flow above that specified in the
Power Setting Table in Section 5 of the AFM/
POH. Continually monitor engine cylinder
head and oil temperatures to avoid exceeding
temperature limits.
srobinson on DSKHWCL6B1PROD with PROPOSALS
Appendix 2 to Docket No. FAA–2010–1295
Model PA–46–350P (Malibu Mirage) and
Model PA–46R–350T (Matrix)—Emergency
Procedures for the Pilot’s Operating
Handbook (POH)
(1) If the turbine inlet temperature
indication fails or is suspected of failure
during takeoff, climb, descent or landing, set
power per the POH Section 5 Power Setting
Table and then lean to the approximate POH
Power Setting Table fuel flow plus 4 GPH.
(2) If the turbine inlet temperature
indication fails or is suspected of failure after
cruise power has been set, maintain the
power setting and increase indicated fuel
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17:52 Dec 29, 2010
Jkt 223001
flow by 1 GPH. Continually monitor engine
cylinder head and oil temperatures to avoid
exceeding temperature limits.
Issued in Kansas City, Missouri on
December 22, 2010.
Earl Lawrence,
Manager, Small Airplane Directorate, Aircraft
Certification Service.
[FR Doc. 2010–32959 Filed 12–29–10; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2010–1206; Directorate
Identifier 2009–NM–216–AD]
RIN 2120–AA64
Airworthiness Directives; McDonnell
Douglas Corporation Model DC–10–10,
DC–10–10F, and MD–10–10F Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to adopt a new
airworthiness directive (AD) for certain
Model DC–10–10, DC–10–10F, and MD–
10–10F airplanes. This proposed AD
would require repetitive inspections for
cracking on the lower cap of the rear
spar of the left and right wings between
stations Xors=417 and the outboard
edge of the lower cap splice of the wing
rear spar at station Xors=400; temporary
and permanent repairs if necessary; and
repetitive inspections of repaired areas
and corrective actions if necessary. This
proposed AD results from reports of
three instances of fuel leaks in the lower
cap splice of the wing rear spar at
station Xors=409. We are proposing this
AD to detect and correct cracking on the
lower cap of the rear spar of the left and
right wings between stations Xors=417
and the outboard edge of the lower cap
splice of the wing rear spar at station
Xors=400, which could result in fuel
leaks or cracking of the lower wing skin
and structure, causing possible inability
of the structure to sustain the limit load
adversely affecting the structural
integrity of the airplane.
DATES: We must receive comments on
this proposed AD by February 14, 2011.
ADDRESSES: You may send comments by
any of the following methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: 202–493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations,
SUMMARY:
PO 00000
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82333
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 proposed AD, contact Boeing
Commercial Airplanes, Attention: Data
& Services Management, 3855
Lakewood Boulevard, MC D800–0019,
Long Beach, California 90846–0001;
telephone 206–544–5000, extension 2;
fax 206–766–5683; e-mail dse.boecom@
boeing.com; Internet https://www.my
boeingfleet.com. You may review copies
of the referenced service information at
the FAA, Transport Airplane
Directorate, 1601 Lind Avenue, SW.,
Renton, Washington. For information on
the availability of this material at the
FAA, call 425–227–1221.
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 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:
Nenita Odesa, Aerospace Engineer,
Airframe Branch, ANM–120L, FAA, Los
Angeles Aircraft Certification Office,
3960 Paramount Boulevard, Lakewood,
California 90712–4137; phone: (562)
627–5234; fax: (562) 627–5210; e-mail:
nenita.odesa@faa.gov.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposed AD. Send your comments
to an address listed under the
ADDRESSES section. Include ‘‘Docket No.
FAA–2010–1206; Directorate Identifier
2009–NM–216–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this proposed AD. We will
consider all comments received by the
closing date and may amend this
proposed AD because of those
comments.
E:\FR\FM\30DEP1.SGM
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82334
Federal Register / Vol. 75, No. 250 / Thursday, December 30, 2010 / Proposed Rules
We will post all comments we
receive, without change, to https://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.
srobinson on DSKHWCL6B1PROD with PROPOSALS
Discussion
We have received reports of three
instances of Model DC–10–10F and
MD–10–10F airplanes having a fuel leak
in the lower cap of the wing rear spar
at station Xors=409. Affected airplanes
had the gross weight doublers installed,
and operators had previously
accomplished Boeing Service Bulletin
DC10–57–138. Investigation revealed
the fuel leak was due to a crack in the
lower cap. This crack extended into all
three legs (aft, forward, and vertical) of
the spar cap. Metallurgical analysis of
the cracked portion of the spar cap
determined that the crack was due to
fatigue and began at a fastener hole in
the aft leg of the spar cap. An
undetected crack in a spar cap, if not
corrected, could lead to fuel leaks or
cracking of the lower wing skin and
structure causing the possible inability
of the structure to sustain the limit load,
and adversely affect the structural
integrity of the airplane.
The design of the spar caps on Model
DC–10–10 airplanes is the same as that
on Model DC–10–10F and MD–10–10F
airplanes in the area of cracking;
therefore, Model DC–10–10 airplanes
are also subject to the identified unsafe
condition.
Relevant Service Information
We have reviewed Boeing Alert
Service Bulletin DC10–57A156,
Revision 1, dated March 10, 2010. The
service bulletin describes procedures for
repetitive eddy current test high
frequency (ETHF) inspections for
cracking on the lower cap of the rear
spar of the left and right wings between
stations Xors=417 and the outboard
edge of the lower cap splice of the wing
rear spar at station Xors=400, and
temporary and permanent repairs, if
necessary. The temporary repair may
only be done on airplanes on which a
crack that extends into the vertical leg
of the spar cap is found and includes
stop drilling the crack and installing an
external doubler. The service bulletin
describes procedures for repetitive
ETHF and ultrasonic inspections for
cracking of the repaired area.
We have also reviewed Boeing DC–
10–10 Service Rework Drawings
SR10570048, Revision J, dated July 16,
2009; which describe procedures for
permanent and temporary repairs. The
type of permanent repair depends on
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17:52 Dec 29, 2010
Jkt 223001
the extent of the cracking and includes
crack removal or stop drill end of the
crack and structural reinforcement. For
permanently and temporarily repaired
areas, the service rework drawing
describes procedures for repetitive
ETHF and ultrasonic inspections for
cracking (depending on the type of
repair that is accomplished).
We have also reviewed Boeing DC–
10–10 Service Rework Drawings
SR10570019, Revision K, dated April
17, 2009, which describe procedures for
permanent repairs. The type of
permanent repair depends on the extent
of the cracking and includes crack
removal or stop drill end of the crack
and structural reinforcement. For
permanently repaired areas, the service
rework drawing describes procedures
for repetitive ETHF and ultrasonic
inspections for cracking (depending on
the type of repair that is accomplished).
FAA’s Determination and Requirements
of This Proposed AD
We are proposing this AD because we
evaluated all relevant information and
determined the unsafe condition
described previously is likely to exist or
develop in other products of the same
type design. This proposed AD would
require accomplishing the actions
specified in the service information
described previously except as
discussed under ‘‘Differences Between
the Proposed AD and the Service
Information.’’
Differences Between the Proposed AD
and the Service Information
Because the service bulletin provides
no corrective action for the post repair
inspections, this AD would require
contacting the FAA.
Costs of Compliance
We estimate that this proposed AD
would affect 68 airplanes of U.S.
registry. We also estimate that it would
take 2 work-hours per product to
comply with this proposed AD. The
average labor rate is $85 per work-hour.
Based on these figures, we estimate the
cost of this proposed AD to the U.S.
operators to be $11,560, or $170 per
product, per inspection cycle.
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,
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Fmt 4702
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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 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 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. 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.
You can find our regulatory
evaluation and the estimated costs of
compliance in the AD Docket.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
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.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new AD:
McDonnell Douglas Corporation: Docket No.
FAA–2010–1206; Directorate Identifier
2009–NM–216–AD.
Comments Due Date
(a) We must receive comments by February
14, 2011.
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Federal Register / Vol. 75, No. 250 / Thursday, December 30, 2010 / Proposed Rules
Affected ADs
(b) None.
Applicability
(c) This AD applies to McDonnell Douglas
Corporation Model DC–10–10, DC–10–10F,
and MD–10–10F airplanes; certificated in any
category; as identified in Boeing Alert
Service Bulletin DC10–57A156, Revision 1,
dated March 10, 2010.
Subject
(d) Air Transport Association (ATA) of
America Code 57: Wings.
Unsafe Condition
(e) This AD results from reports of three
instances of fuel leaks in the lower cap splice
of the wing rear spar at station Xors=409. The
Federal Aviation Administration is issuing
this AD to detect and correct cracking on the
lower cap of the rear spar of the left and right
wings between stations Xors=417 and the
outboard edge of the lower cap splice of the
wing rear spar at station Xors=400, which
could result in fuel leaks or cracking of the
lower wing skin and structure, causing
possible inability to sustain the limit load
and adversely affecting the structural
integrity of the airplane.
srobinson on DSKHWCL6B1PROD with PROPOSALS
Compliance
(f) You are responsible for having the
actions required by this AD performed within
the compliance times specified, unless the
actions have already been done.
Inspection
(g) Within 1,750 flight cycles after the
effective date of this AD, do an eddy current
test high frequency (ETHF) inspection for
cracking on the lower cap of the rear spar of
the left and right wings between stations
Xors=417 and the outboard edge of the lower
cap splice of the wing rear spar at station
Xors=400, in accordance with the
Accomplishment Instructions of Boeing Alert
Service Bulletin DC10–57A156, Revision 1,
dated March 10, 2010.
(1) If no cracking is found, repeat the
inspection required by paragraph (g) of this
AD thereafter at intervals not to exceed 1,750
flight cycles.
(2) If any cracking is found in the spar cap
aft leg at the fastener holes, and that cracking
can be removed by hole enlargement, before
further flight, do a permanent repair, in
accordance with Boeing DC–10–10 Service
Rework Drawing SR10570048, Revision J,
dated July 16, 2009. Within 1,750 flight
cycles after doing the applicable permanent
repair, and thereafter at intervals not to
exceed 1,750 flight cycles, do an ETHF
inspection for cracking in accordance with
Boeing DC–10–10 Service Rework Drawing
SR10570048, Revision J, dated July 16, 2009.
If any cracking is found during any
inspection required by this paragraph, before
further flight, repair the cracking, in
accordance with the procedures specified in
paragraph (i) of this AD.
(3) If any cracking is found in the spar cap
aft leg at the fastener holes, and that cracking
cannot be removed by hole enlargement but
it does not extend into the vertical leg, before
further flight, do a permanent repair, in
VerDate Mar<15>2010
17:52 Dec 29, 2010
Jkt 223001
82335
accordance with Boeing DC–10–10 Service
Rework Drawing SR10570048, Revision J,
dated July 16, 2009. Within 4,550 flight
cycles after doing a permanent repair, and
thereafter at intervals not to exceed 4,550
flight cycles, do ETHF and ultrasonic
inspections for cracking, in accordance with
Boeing DC–10–10 Service Rework Drawing
SR10570048, Revision J, dated July 16, 2009.
If any cracking is found during any
inspection required by this paragraph, before
further flight, repair the cracking, in
accordance with the procedures specified in
paragraph (i) of this AD.
(4) If any cracking is found in the spar cap
aft leg at fastener holes and that cracking
extends into the vertical leg of the spar cap,
do the actions specified in paragraph (g)(4)(i)
or (g)(4)(ii) of this AD.
(i) Do the actions in paragraphs (g)(4)(i)(A)
and (g)(4)(i)(B) of this AD.
(A) Before further flight, do a temporary
repair in accordance with Boeing DC–10–10
Service Rework Drawing SR10570048,
Revision J, dated July 16, 2009. Within 1,650
flight cycles after doing the temporary repair;
and thereafter at intervals not to exceed 1,650
flight cycles, do ETHF and ultrasonic
inspections for cracking of the repaired area,
in accordance with Boeing DC–10–10 Service
Rework Drawing SR10570048, Revision J,
dated July 16, 2009, until the permanent
repair required by paragraph (g)(4)(i)(B) of
this AD is done. If any cracking is found
during any inspection required by this
paragraph, before further flight, repair the
cracking, in accordance with the procedures
specified in paragraph (i) of this AD.
(B) Within 7,000 flight cycles after the
temporary repair has been done, do the
applicable permanent repair, in accordance
with Boeing DC–10–10 Service Rework
Drawing SR10570019, Revision K, dated
April 17, 2009. Within 4,550 flight cycles
after doing the permanent repair; and
thereafter at intervals not to exceed 4,550
flight cycles; do ETHF and ultrasonic
inspections for cracking of the repaired area,
in accordance with Boeing DC–10–10 Service
Rework Drawing SR10570019, Revision K,
dated April 17, 2009. If any cracking is found
during any inspection required by this
paragraph, before further flight, repair the
cracking, in accordance with the procedures
specified in paragraph (i) of this AD.
(ii) Before further flight do the applicable
permanent repair, in accordance with Boeing
DC–10–10 Service Rework Drawing
SR10570019, Revision K, dated April 17,
2009. Within 4,550 flight cycles after doing
the permanent repair; and thereafter at
intervals not to exceed 4,550 flight cycles, do
ETHF and ultrasonic inspections for cracking
of the repaired area, in accordance with
Boeing DC–10–10 Service Rework Drawing
SR10570019, Revision K, dated April 17,
2009. If any cracking is found during any
inspection required by this paragraph, before
further flight, repair the cracking, in
accordance with the procedures specified in
paragraph (i) of this AD.
Alert Service Bulletin DC10–57A156, dated
September 16, 2009, are considered
acceptable for compliance with the
corresponding actions specified in this AD.
Credit for Actions Accomplished in
Accordance With Previous Service
Information
(h) Actions accomplished before the
effective date of this AD according to Boeing
SUMMARY:
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Alternative Methods of Compliance
(AMOCs)
(i)(1) The Manager, Los Angeles Aircraft
Certification Office, (ACO) FAA, has the
authority to approve AMOCs for this AD, if
requested using the procedures found in 14
CFR 39.19. Send information to ATTN:
Nenita Odesa, Aerospace Engineer, Airframe
Branch, ANM–120L, FAA, Los Angeles ACO,
3960 Paramount Boulevard, Lakewood,
California 90712–4137; phone: (562) 627–
5234; fax: (562) 627–5210; e-mail: nenita.
odessa@faa.gov.
(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 principal maintenance inspector
(PMI) or principal avionics inspector (PAI),
as appropriate, or lacking a principal
inspector, your local Flight Standards District
Office. The AMOC approval letter must
specifically reference this AD.
(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 the
Boeing Commercial Airplanes Organization
Designation Authorization (ODA) that 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.
Issued in Renton, Washington, on
December 17, 2010.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2010–33001 Filed 12–29–10; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2010–1296; Directorate
Identifier 2010–CE–063–AD]
RIN 2120–AA64
Airworthiness Directives; APEX
Aircraft Model CAP 10 Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to adopt a new
airworthiness directive (AD) for the
products listed above. This proposed
AD results from mandatory continuing
airworthiness information (MCAI)
E:\FR\FM\30DEP1.SGM
30DEP1
Agencies
[Federal Register Volume 75, Number 250 (Thursday, December 30, 2010)]
[Proposed Rules]
[Pages 82333-82335]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2010-33001]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2010-1206; Directorate Identifier 2009-NM-216-AD]
RIN 2120-AA64
Airworthiness Directives; McDonnell Douglas Corporation Model DC-
10-10, DC-10-10F, and MD-10-10F Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to adopt a new airworthiness directive (AD) for
certain Model DC-10-10, DC-10-10F, and MD-10-10F airplanes. This
proposed AD would require repetitive inspections for cracking on the
lower cap of the rear spar of the left and right wings between stations
Xors=417 and the outboard edge of the lower cap splice of the wing rear
spar at station Xors=400; temporary and permanent repairs if necessary;
and repetitive inspections of repaired areas and corrective actions if
necessary. This proposed AD results from reports of three instances of
fuel leaks in the lower cap splice of the wing rear spar at station
Xors=409. We are proposing this AD to detect and correct cracking on
the lower cap of the rear spar of the left and right wings between
stations Xors=417 and the outboard edge of the lower cap splice of the
wing rear spar at station Xors=400, which could result in fuel leaks or
cracking of the lower wing skin and structure, causing possible
inability of the structure to sustain the limit load adversely
affecting the structural integrity of the airplane.
DATES: We must receive comments on this proposed AD by February 14,
2011.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Portal: Go to https://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 proposed AD, contact
Boeing Commercial Airplanes, Attention: Data & Services Management,
3855 Lakewood Boulevard, MC D800-0019, Long Beach, California 90846-
0001; telephone 206-544-5000, extension 2; fax 206-766-5683; e-mail
dse.boecom@boeing.com; Internet https://www.myboeingfleet.com. You may
review copies of the referenced service information at the FAA,
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton,
Washington. For information on the availability of this material at the
FAA, call 425-227-1221.
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 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: Nenita Odesa, Aerospace Engineer,
Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification
Office, 3960 Paramount Boulevard, Lakewood, California 90712-4137;
phone: (562) 627-5234; fax: (562) 627-5210; e-mail:
nenita.odesa@faa.gov.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2010-1206;
Directorate Identifier 2009-NM-216-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD because of those comments.
[[Page 82334]]
We will post all comments we receive, without change, to https://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
We have received reports of three instances of Model DC-10-10F and
MD-10-10F airplanes having a fuel leak in the lower cap of the wing
rear spar at station Xors=409. Affected airplanes had the gross weight
doublers installed, and operators had previously accomplished Boeing
Service Bulletin DC10-57-138. Investigation revealed the fuel leak was
due to a crack in the lower cap. This crack extended into all three
legs (aft, forward, and vertical) of the spar cap. Metallurgical
analysis of the cracked portion of the spar cap determined that the
crack was due to fatigue and began at a fastener hole in the aft leg of
the spar cap. An undetected crack in a spar cap, if not corrected,
could lead to fuel leaks or cracking of the lower wing skin and
structure causing the possible inability of the structure to sustain
the limit load, and adversely affect the structural integrity of the
airplane.
The design of the spar caps on Model DC-10-10 airplanes is the same
as that on Model DC-10-10F and MD-10-10F airplanes in the area of
cracking; therefore, Model DC-10-10 airplanes are also subject to the
identified unsafe condition.
Relevant Service Information
We have reviewed Boeing Alert Service Bulletin DC10-57A156,
Revision 1, dated March 10, 2010. The service bulletin describes
procedures for repetitive eddy current test high frequency (ETHF)
inspections for cracking on the lower cap of the rear spar of the left
and right wings between stations Xors=417 and the outboard edge of the
lower cap splice of the wing rear spar at station Xors=400, and
temporary and permanent repairs, if necessary. The temporary repair may
only be done on airplanes on which a crack that extends into the
vertical leg of the spar cap is found and includes stop drilling the
crack and installing an external doubler. The service bulletin
describes procedures for repetitive ETHF and ultrasonic inspections for
cracking of the repaired area.
We have also reviewed Boeing DC-10-10 Service Rework Drawings
SR10570048, Revision J, dated July 16, 2009; which describe procedures
for permanent and temporary repairs. The type of permanent repair
depends on the extent of the cracking and includes crack removal or
stop drill end of the crack and structural reinforcement. For
permanently and temporarily repaired areas, the service rework drawing
describes procedures for repetitive ETHF and ultrasonic inspections for
cracking (depending on the type of repair that is accomplished).
We have also reviewed Boeing DC-10-10 Service Rework Drawings
SR10570019, Revision K, dated April 17, 2009, which describe procedures
for permanent repairs. The type of permanent repair depends on the
extent of the cracking and includes crack removal or stop drill end of
the crack and structural reinforcement. For permanently repaired areas,
the service rework drawing describes procedures for repetitive ETHF and
ultrasonic inspections for cracking (depending on the type of repair
that is accomplished).
FAA's Determination and Requirements of This Proposed AD
We are proposing this AD because we evaluated all relevant
information and determined the unsafe condition described previously is
likely to exist or develop in other products of the same type design.
This proposed AD would require accomplishing the actions specified in
the service information described previously except as discussed under
``Differences Between the Proposed AD and the Service Information.''
Differences Between the Proposed AD and the Service Information
Because the service bulletin provides no corrective action for the
post repair inspections, this AD would require contacting the FAA.
Costs of Compliance
We estimate that this proposed AD would affect 68 airplanes of U.S.
registry. We also estimate that it would take 2 work-hours per product
to comply with this proposed AD. The average labor rate is $85 per
work-hour. Based on these figures, we estimate the cost of this
proposed AD to the U.S. operators to be $11,560, or $170 per product,
per inspection cycle.
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 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 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. 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.
You can find our regulatory evaluation and the estimated costs of
compliance in the AD Docket.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, 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 FAA amends Sec. 39.13 by adding the following new AD:
McDonnell Douglas Corporation: Docket No. FAA-2010-1206; Directorate
Identifier 2009-NM-216-AD.
Comments Due Date
(a) We must receive comments by February 14, 2011.
[[Page 82335]]
Affected ADs
(b) None.
Applicability
(c) This AD applies to McDonnell Douglas Corporation Model DC-
10-10, DC-10-10F, and MD-10-10F airplanes; certificated in any
category; as identified in Boeing Alert Service Bulletin DC10-
57A156, Revision 1, dated March 10, 2010.
Subject
(d) Air Transport Association (ATA) of America Code 57: Wings.
Unsafe Condition
(e) This AD results from reports of three instances of fuel
leaks in the lower cap splice of the wing rear spar at station
Xors=409. The Federal Aviation Administration is issuing this AD to
detect and correct cracking on the lower cap of the rear spar of the
left and right wings between stations Xors=417 and the outboard edge
of the lower cap splice of the wing rear spar at station Xors=400,
which could result in fuel leaks or cracking of the lower wing skin
and structure, causing possible inability to sustain the limit load
and adversely affecting the structural integrity of the airplane.
Compliance
(f) You are responsible for having the actions required by this
AD performed within the compliance times specified, unless the
actions have already been done.
Inspection
(g) Within 1,750 flight cycles after the effective date of this
AD, do an eddy current test high frequency (ETHF) inspection for
cracking on the lower cap of the rear spar of the left and right
wings between stations Xors=417 and the outboard edge of the lower
cap splice of the wing rear spar at station Xors=400, in accordance
with the Accomplishment Instructions of Boeing Alert Service
Bulletin DC10-57A156, Revision 1, dated March 10, 2010.
(1) If no cracking is found, repeat the inspection required by
paragraph (g) of this AD thereafter at intervals not to exceed 1,750
flight cycles.
(2) If any cracking is found in the spar cap aft leg at the
fastener holes, and that cracking can be removed by hole
enlargement, before further flight, do a permanent repair, in
accordance with Boeing DC-10-10 Service Rework Drawing SR10570048,
Revision J, dated July 16, 2009. Within 1,750 flight cycles after
doing the applicable permanent repair, and thereafter at intervals
not to exceed 1,750 flight cycles, do an ETHF inspection for
cracking in accordance with Boeing DC-10-10 Service Rework Drawing
SR10570048, Revision J, dated July 16, 2009. If any cracking is
found during any inspection required by this paragraph, before
further flight, repair the cracking, in accordance with the
procedures specified in paragraph (i) of this AD.
(3) If any cracking is found in the spar cap aft leg at the
fastener holes, and that cracking cannot be removed by hole
enlargement but it does not extend into the vertical leg, before
further flight, do a permanent repair, in accordance with Boeing DC-
10-10 Service Rework Drawing SR10570048, Revision J, dated July 16,
2009. Within 4,550 flight cycles after doing a permanent repair, and
thereafter at intervals not to exceed 4,550 flight cycles, do ETHF
and ultrasonic inspections for cracking, in accordance with Boeing
DC-10-10 Service Rework Drawing SR10570048, Revision J, dated July
16, 2009. If any cracking is found during any inspection required by
this paragraph, before further flight, repair the cracking, in
accordance with the procedures specified in paragraph (i) of this
AD.
(4) If any cracking is found in the spar cap aft leg at fastener
holes and that cracking extends into the vertical leg of the spar
cap, do the actions specified in paragraph (g)(4)(i) or (g)(4)(ii)
of this AD.
(i) Do the actions in paragraphs (g)(4)(i)(A) and (g)(4)(i)(B)
of this AD.
(A) Before further flight, do a temporary repair in accordance
with Boeing DC-10-10 Service Rework Drawing SR10570048, Revision J,
dated July 16, 2009. Within 1,650 flight cycles after doing the
temporary repair; and thereafter at intervals not to exceed 1,650
flight cycles, do ETHF and ultrasonic inspections for cracking of
the repaired area, in accordance with Boeing DC-10-10 Service Rework
Drawing SR10570048, Revision J, dated July 16, 2009, until the
permanent repair required by paragraph (g)(4)(i)(B) of this AD is
done. If any cracking is found during any inspection required by
this paragraph, before further flight, repair the cracking, in
accordance with the procedures specified in paragraph (i) of this
AD.
(B) Within 7,000 flight cycles after the temporary repair has
been done, do the applicable permanent repair, in accordance with
Boeing DC-10-10 Service Rework Drawing SR10570019, Revision K, dated
April 17, 2009. Within 4,550 flight cycles after doing the permanent
repair; and thereafter at intervals not to exceed 4,550 flight
cycles; do ETHF and ultrasonic inspections for cracking of the
repaired area, in accordance with Boeing DC-10-10 Service Rework
Drawing SR10570019, Revision K, dated April 17, 2009. If any
cracking is found during any inspection required by this paragraph,
before further flight, repair the cracking, in accordance with the
procedures specified in paragraph (i) of this AD.
(ii) Before further flight do the applicable permanent repair,
in accordance with Boeing DC-10-10 Service Rework Drawing
SR10570019, Revision K, dated April 17, 2009. Within 4,550 flight
cycles after doing the permanent repair; and thereafter at intervals
not to exceed 4,550 flight cycles, do ETHF and ultrasonic
inspections for cracking of the repaired area, in accordance with
Boeing DC-10-10 Service Rework Drawing SR10570019, Revision K, dated
April 17, 2009. If any cracking is found during any inspection
required by this paragraph, before further flight, repair the
cracking, in accordance with the procedures specified in paragraph
(i) of this AD.
Credit for Actions Accomplished in Accordance With Previous Service
Information
(h) Actions accomplished before the effective date of this AD
according to Boeing Alert Service Bulletin DC10-57A156, dated
September 16, 2009, are considered acceptable for compliance with
the corresponding actions specified in this AD.
Alternative Methods of Compliance (AMOCs)
(i)(1) The Manager, Los Angeles Aircraft Certification Office,
(ACO) FAA, has the authority to approve AMOCs for this AD, if
requested using the procedures found in 14 CFR 39.19. Send
information to ATTN: Nenita Odesa, Aerospace Engineer, Airframe
Branch, ANM-120L, FAA, Los Angeles ACO, 3960 Paramount Boulevard,
Lakewood, California 90712-4137; phone: (562) 627-5234; fax: (562)
627-5210; e-mail: nenita.odessa@faa.gov.
(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 principal maintenance inspector (PMI) or
principal avionics inspector (PAI), as appropriate, or lacking a
principal inspector, your local Flight Standards District Office.
The AMOC approval letter must specifically reference this AD.
(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 the
Boeing Commercial Airplanes Organization Designation Authorization
(ODA) that 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.
Issued in Renton, Washington, on December 17, 2010.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2010-33001 Filed 12-29-10; 8:45 am]
BILLING CODE 4910-13-P