Airworthiness Directives; The Boeing Company Airplanes, 73739-73742 [2013-29317]
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maindgalligan on DSK5TPTVN1PROD with PROPOSALS
Federal Register / Vol. 78, No. 236 / Monday, December 9, 2013 / Proposed Rules
DOE is also interested in comments on
other relevant issues that participants
believe would affect energy
conservation standards for these
products, applicable test procedures, or
the preliminary determination on the
scope of coverage. DOE invites all
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submit in writing by January 23, 2014,
comments and information on matters
addressed in the Framework Document
and on other matters relevant to DOE’s
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appliance_standards/
product.aspx?productid=82.
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for determining whether to establish or
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Issued in Washington, DC, on December 2,
2013.
Kathleen B. Hogan,
Deputy Assistant Secretary for Energy
Efficiency, Energy Efficiency and Renewable
Energy.
[FR Doc. 2013–29166 Filed 12–6–13; 8:45 am]
BILLING CODE 6450–01–P
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2013–0981; Directorate
Identifier 2013–NM–032–AD]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to supersede
Airworthiness Directives (ADs) 97–11–
07 and AD 99–18–23, which apply to all
The Boeing Company Model MD–90–30
airplanes. AD 97–11–07 and AD 99–18–
23 currently require revising the
Airworthiness Limitations Section
(ALS) of the Instructions for Continued
Airworthiness to incorporate certain
compliance times for principal
structural elements (PSE) inspections
and replacement times for safe-life
limited parts. Since we issued AD 97–
11–07 and AD 99–18–23, an analysis of
data identified a need to introduce a
new PSE requirement for the rear spar
caps of the horizontal stabilizer. This
proposed AD would require revising the
maintenance or inspection program to
incorporate the new PSE requirement
and its associated inspections. We are
proposing this AD to detect and correct
fatigue cracking of PSEs and certain
safe-life limited parts, which could
adversely affect the structural integrity
of the airplane.
DATES: We must receive comments on
this proposed AD by January 23, 2014.
ADDRESSES: You may send comments,
using the procedures found in 14 CFR
11.43 and 11.45, 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: Deliver to Mail
address above 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, CA 90846–0001; telephone
SUMMARY:
PO 00000
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73739
206–544–5000, extension 2; fax 206–
766–5683; Internet https://
www.myboeingfleet.com. You may view
this 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
(phone: 800–647–5527) is in the
ADDRESSES section. Comments will be
available in the AD docket shortly after
receipt.
FOR FURTHER INFORMATION CONTACT:
Roger Durbin, Airframe Branch, ANM–
120L, FAA, Los Angeles Aircraft
Certification Office (ACO), 3960
Paramount Boulevard, Lakewood,
California 90712–4137; phone: (562)
627–5233; fax: (562) 627–5210; email:
roger.durbin@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–2013–0981; Directorate Identifier
2013–NM–032–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.
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
On May 16, 1997, we issued AD 97–
11–07, Amendment 39–10036 (62 FR
27941, May 22, 1997), for all The Boeing
Company Model MD–90–30 airplanes.
AD 97–11–07 requires revising the
Airworthiness Limitations Section of
the Instructions for Continued
Airworthiness (MD–90–30
Airworthiness Limitations Instructions
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(ALI)) to add principle structural
elements (PSE) requirements. AD 97–
11–07 resulted from analysis of data that
identified reduced initial inspection
thresholds, reduced repetitive
inspection intervals for PSEs, and other
PSEs to be added to the ALI. We issued
AD 97–11–07 to detect and correct
fatigue cracking, which could result in
reduced structural integrity or reduced
controllability of the airplane.
On August 27, 1999, we issued AD
99–18–23, Amendment 39–11289 (64
FR 48284, September 3, 1999), for all
The Boeing Company Model MD–90–30
airplanes. AD 99–18–23 requires
revising the Airworthiness Limitations
Section of the Instructions for
Continued Airworthiness (MD–90–30
Airworthiness Limitations Instructions
(ALI)) to incorporate certain
replacement times for safe-life limited
parts. AD 99–18–23 resulted from
analysis of data that identified reduced
replacement times for certain safe-life
limited parts. We issued AD 99–18–23
to prevent fatigue cracking of various
safe-life limited parts, which could
adversely affect the structural integrity
of airplanes.
Actions Since Existing AD Was Issued
Since we issued AD 97–11–07,
Amendment 39–10036 (62 FR 27941,
May 22, 1997), and AD 99–18–23,
Amendment 39–11289 (64 FR 48284,
September 3, 1999), an analysis of data
identified the need to introduce a new
principle structural elements (PSE)
requirement for the rear spar of the
horizontal stabilizer and its associated
inspections.
Relevant Service Information
We reviewed Boeing MD–90
Airworthiness Limitations Instructions
(ALI) Report No. MDC–94K9000,
Revision 6, dated September 2011. For
information on the procedures and
compliance times, see this service
information at https://
www.regulations.gov by searching for
Docket No. FAA–2013–0981.
FAA’s Determination
We are proposing this AD because we
evaluated all the relevant information
and determined the unsafe condition
described previously is likely to exist or
develop in other products of the same
type design.
This AD requires revisions to certain
operator maintenance documents to
include new actions (e.g., inspections).
Compliance with these actions is
required by 14 CFR 91.403(c). For
airplanes that have been previously
modified, altered, or repaired in the
areas addressed by this AD, the operator
may not be able to accomplish the
actions described in the revisions. In
this situation, to comply with 14 CFR
91.403(c), the operator must request
approval for an alternative method of
compliance according to paragraph (n)
of this proposed AD. The request should
include a description of changes to the
required actions that will ensure the
continued damage tolerance of the
affected structure.
Proposed AD Requirements
This proposed AD would retain all of
the requirements of AD 97–11–07,
Amendment 39–10036 (62 FR 27941,
May 22, 1997), and AD 99–18–23,
Amendment 39–11289 (64 FR 48284,
September 3, 1999). This proposed AD
would require revising the maintenance
program to incorporate the new PSE
requirement and its associated
inspections.
Costs of Compliance
We estimate that this proposed AD
affects 52 airplanes of U.S. registry.
We estimate the following costs to
comply with this proposed AD:
ESTIMATED COSTS
Cost per
product
Labor cost
Revise airworthiness limitations [retained actions from AD 97–11–07, Amendment 39–
10036 (62 FR 27941, May 22, 1997).
Revise airworthiness limitations [retained actions from AD 99–18–23, Amendment 39–
11289 (64 FR 48284, September 3, 1999).
Revise airworthiness limitations [new proposed action].
1 work-hour × $85 per hour = $85 .................
$0
$85
$35,445
1 work-hour × 85 per hour = 85 .....................
0
85
35,445
1 work-hour × 85 per hour = 85 .....................
0
85
35,445
maindgalligan on DSK5TPTVN1PROD 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
the Administrator finds necessary for
safety in air commerce. This regulation
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Parts cost
Cost on U.S.
operators
Action
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
Regulatory Findings
We have determined that this
proposed AD would not have federalism
implications under Executive Order
13132. This proposed AD would not
have a substantial direct effect on the
States, on the relationship between the
national Government and the States, or
on the distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that the proposed regulation:
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(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),
(3) Will not affect intrastate aviation
in Alaska, and
(4) 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.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
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Federal Register / Vol. 78, No. 236 / Monday, December 9, 2013 / Proposed Rules
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:
a. Removing airworthiness directive
(AD) 97–11–07, Amendment 39–10036
(62 FR 27941, May 22, 1997), and AD
99–18–23, Amendment 39–11289 (64
FR 48284, September 3, 1999), and
■ b. Adding the following new AD:
■
■
The Boeing Company: Docket No. FAA–
2013–0981; Directorate Identifier 2013–NM–
032–AD.
(a) Comments Due Date
The FAA must receive comments on this
AD action by January 23, 2014.
(b) Affected ADs
This AD supersedes AD 97–11–07,
Amendment 39–10036 (62 FR 27941, May 22,
1997), and AD 99–18–23, Amendment 39–
11289 (64 FR 48284, September 3, 1999).
(c) Applicability
This AD applies to all The Boeing
Company Model MD–90–30 airplanes,
certificated in any category.
(d) Subject
Air Transport Association (ATA) of
America Code 51, Standard Practices/
Structures; Code 55, Stabilizers.
(e) Unsafe Condition
This AD was prompted by an analysis of
data that identified a need to introduce a new
principal structural elements (PSE)
requirement for the rear spar caps of the
horizontal stabilizer. We are issuing this AD
to detect and correct fatigue cracking of PSEs
and certain safe-life limited parts, which
could adversely affect the structural integrity
of the airplane.
maindgalligan on DSK5TPTVN1PROD with PROPOSALS
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Retained Revision of Airworthiness
Limitations of Principal Structural Elements
This paragraph restates the requirements of
paragraph (a) of AD 97–11–07, Amendment
39–10036 (62 FR 27941, May 22, 1997).
Within 180 days after June 26, 1997 (the
effective date of AD 97–11–07, Amendment
39–10036 (62 FR 27941, May 22, 1997)),
revise the Airworthiness Limitations Section
of the Instructions for Continued
Airworthiness (Airworthiness Limitations
Instructions (ALI), McDonnell Douglas
Report No. MDC–94K9000, dated November
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1994) to incorporate the Item, Location, and
Inspection Interval of principal structural
elements identified in paragraphs (g)(1)
through (g)(3) of this AD. This may be
accomplished by inserting a copy of Revision
1 of the ALI, dated January 1995; or a copy
of this AD into the ALI.
(1) For Item 53.30.02.3 at Skin Panels, STA
237 to 1395 Fuselage Skin in Constant
Section from Longeron 3 Left to Longeron 3
Right: Initial Interval at 60,000 landings.
Repeat the inspection thereafter at intervals
not to exceed 11,000 landings.
(2) For Item 53.30.02.4 at Skin Panels, STA
237 to 1395 Fuselage Hoop Skin Splice in
Constant Section from Longeron 5 Left to
Longeron 5 Right: Initial Interval at 60,000
landings. Repeat the inspection thereafter at
intervals not to exceed 30,000 landings.
(3) For Item 54.10.04.1 at Thrust Bulkhead,
Pylon—STA Yn 170.5—Rear Spar and Engine
Thrust Support Fitting (Upper and Lower):
Initial Interval at 15,000 landings. Repeat the
inspection thereafter at intervals not to
exceed 4,500 landings.
(h) Retained Revision of Airworthiness
Limitations
(1) This paragraph restates the
requirements of paragraph (b) of AD 97–11–
07, Amendment 39–10036 (62 FR 27941, May
22, 1997). Within 180 days after June 26,
1997 (the effective date of AD 97–11–07,
Amendment 39–10036 (62 FR 27941, May 22,
1997)), revise the Airworthiness Limitations
Section of the Instructions for Continued
Airworthiness (Airworthiness Limitations
Instructions (ALI), McDonnell Douglas
Report No. MDC–94K9000, dated November
1994) to incorporate the Item, Location, and
Inspection Interval of principal structural
element specified in paragraph (h)(2) of this
AD. This may be accomplished by inserting
a copy of Revision 2 to the ALI, dated July
1996, or a copy this AD into the ALI or
Airworthiness Limitations Section.
(2) For Item 55.13.01.1 at Plates/Skin—
Upper STA Xh 27.2 Left to Xh 27.2 Right—
Upper Aft Skin Plank with Integral Stringers
from Xh 7.234 to Xh 26.859: Initial Interval
at 60,000 landings. Repeat the inspection
thereafter at intervals not to exceed 8,100
landings.
(i) Retained Restriction on Alternative
Inspections and Inspection Intervals
This paragraph restates the restriction on
alternative inspections and inspection
intervals required by paragraph (c) of AD 97–
11–07, Amendment 39–10036 (62 FR 27941,
May 22, 1997). Except as provided by
paragraphs (l) and (n) of this AD:
After the actions required by paragraphs (g)
and (h) of this AD have been accomplished,
no alternative inspections or inspection
intervals may be approved for the parts
specified in paragraphs (g) and (h) of this AD.
(j) Retained Revision of Airworthiness
Limitations of Safe-Life Limited Parts:
This paragraph restates the requirements of
paragraph (a) of AD 99–18–23, Amendment
39–11289 (64 FR 48284, September 3, 1999).
Within 180 days after October 8, 1999 (the
effective date of AD 99–18–23, Amendment
39–48284 (64 FR 48284, September 3, 1999)),
revise the Airworthiness Limitations Section
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73741
of the Instructions for Continued
Airworthiness (Airworthiness Limitations
Instructions (ALI), McDonnell Douglas
Report No. MDC–94K9000, dated November
1994) to incorporate the Part Number, Item,
and Mandatory Replacement Time of certain
safe-life limited parts by inserting a copy of
Revision 3, to the ALI, dated November 1997,
into the ALI.
(k) Retained Restriction on Alternative
Inspections and Inspection Intervals
This paragraph restates the restriction on
alternative inspections and inspection
intervals required by paragraph (b) of AD 99–
18–23, Amendment 39–11289 (64 FR 48284,
September 3, 1999). Except as provided by
paragraphs (l) and (n) of this AD: After the
actions required by paragraph (j) of this AD
have been accomplished, no alternative
replacement times for the safe-life limited
parts specified in McDonnell Douglas ALI
Report No. MDC–94K9000, Revision 3, dated
November 1997.
(l) New Requirements of This AD: Revision
of the Maintenance Program
(1) Within 180 days after the effective date
of this AD, revise the maintenance or
inspection program, as applicable, to
incorporate the tasks specified in
Airworthiness Limitations Instructions (ALI),
Boeing Report No. MDC–94K9000, Revision
6, dated September 2011. The compliance
times for the initial and repetitive intervals
for the tasks are stated in Airworthiness
Limitations Instructions (ALI), Boeing Report
No. MDC–94K9000, Revision 6, dated
September 2011. Doing the revision required
by this paragraph terminates the revisions
required by paragraphs (g), (h), and (j) of this
AD.
(m) No Alternative Actions or Intervals
After accomplishing the revision required
by paragraph (l) of this AD, no alternative
actions (e.g., inspections) or intervals may be
used unless the actions or intervals are
approved as an alternative method of
compliance (AMOC) in accordance with the
procedures specified in paragraph (n) of this
AD.
(n) Alternative Methods of Compliance
(AMOCs)
(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. 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
paragraph (o) of this AD.
(2) Before using any approved AMOC,
notify your appropriate principal inspector,
or lacking a principal inspector, the manager
of the local flight standards district office/
certificate holding district office.
(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
Boeing Commercial Airplanes Organization
Designation Authorization (ODA) that has
been authorized by the Manager, Los Angeles
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ACO to make those findings. For a repair
method to be approved, the repair must meet
the certification basis of the airplane and the
approval must specifically refer to this AD.
(4) AMOCs approved for AD 97–11–07,
Amendment 39–10036 (62 FR 27941, May 22,
1997), and AD 99–18–23, Amendment 39–
11289 (64 FR 48284, September 3, 1999), are
approved as AMOCs for the corresponding
provisions of this AD.
(o) Related Information
(1) For more information about this AD,
contact Roger Durbin, Airframe Branch,
ANM–120L, FAA, Los Angeles Aircraft
Certification Office (ACO), 3960 Paramount
Boulevard, Lakewood, California 90712–
4137; phone: (562) 627–5233; fax: (562) 627–
5210; email: roger.durbin@faa.gov.
(2) For service information identified in
this AD, contact Boeing Commercial
Airplanes, Attention: Data & Services
Management, 3855 Lakewood Boulevard, MC
D800–0019, Long Beach, CA 90846–0001;
telephone 206–544–5000, extension 2; fax
206–766–5683; Internet https://
www.myboeingfleet.com. You may view this
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.
Issued in Renton, Washington, on
November 29, 2013.
John P. Piccola,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2013–29317 Filed 12–6–13; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2013–0980; Directorate
Identifier 2013–NM–129–AD]
RIN 2120–AA64
Airworthiness Directives; EADS CASA
(Type Certificate Previously Held by
Construcciones Aeronauticas, S.A.)
Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to adopt a new
airworthiness directive (AD) for certain
EADS CASA (Type Certificate
Previously Held by Construcciones
Aeronauticas, S.A.) Model CN–235–300
airplanes. This proposed AD was
prompted by reports of reduced
thickness of the center fuselage lower
skin panel. This proposed AD would
require a detailed inspection to
determine the presence of panel
maindgalligan on DSK5TPTVN1PROD with PROPOSALS
SUMMARY:
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thickness reduction, and repetitive
nondestructive testing (NDT)
inspections and repair if necessary. We
are proposing this AD to detect and
correct a reduced thickness of lower
panel joints, which could result in
reduced fatigue and damage tolerant
characteristics of the lower panel joint
to the adjacent side panels and lead to
failure of the center fuselage lower skin
panel, resulting in loss of control of the
airplane.
DATES: We must receive comments on
this proposed AD by January 23, 2014.
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, between
9 a.m. and 5 p.m., Monday through
Friday, except Federal holidays.
For service information identified in
this proposed AD, contact EADS–CASA,
Military Transport Aircraft Division
(MTAD), Integrated Customer Services
(ICS), Technical Services, Avenida de
´
Aragon 404, 28022 Madrid, Spain;
telephone +34 91 585 55 84; fax +34 91
585 55 05; email
MTA.TechnicalService@casa.eads.net;
Internet https://www.eads.net. You may
view this referenced service information
at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue SW.,
Renton, WA. 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 Operations office 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 Operations
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:
Shahram Daneshmandi, Aerospace
Engineer, International Branch, ANM–
116, Transport Airplane Directorate,
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FAA, 1601 Lind Avenue SW., Renton,
Washington 98057–3356; telephone
(425) 227–1112; fax (425) 227–1149.
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–2013–0980; Directorate Identifier
2013–NM–129–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 based on those comments.
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
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Community, has issued EASA
Airworthiness Directive 2013–0131,
dated June 25, 2013 (referred to after
this as the Mandatory Continuing
Airworthiness Information, or ‘‘the
MCAI’’), to correct an unsafe condition
for the specified products. The MCAI
states:
During delivery of a spare centre fuselage
lower skin panel to a CN–235 aeroplane
operator, a reduced thickness of the spare
panel was identified. The affected panel is
used as the lower part of the fuselage
between Frame (FR) FR13 and FR21, and
from Stringer (STR) 24 left hand (LH) side to
STR24 right hand (RH) side. Several CN–235
aeroplanes could have been delivered with a
reduced thickness panel.
This condition, if not detected and
corrected, could result in reduced fatigue and
damage tolerant characteristics of the lower
panel joint to the adjacent side panels and
lead to failure of the part.
To address this potentially unsafe
condition, EADS–CASA issued All Operator
Letter (AOL) 235–024 to provide instructions
to determine correct centre fuselage lower
panel configuration by accomplishing a
detailed visual inspection (DVI) of affected
fuselage area [for any cracking].
For the reason described above, this
[EASA] AD requires a one-time inspection of
the affected panel thickness at STR24 LH and
STR24 RH. In case a nonconforming panel is
found to be installed, this [EASA] AD
requires repetitive Non Destructive Testing
(NDT) inspections and, depending on
findings, the accomplishment of applicable
corrective action(s).
E:\FR\FM\09DEP1.SGM
09DEP1
]]>Agencies
[Federal Register Volume 78, Number 236 (Monday, December 9, 2013)]
[Proposed Rules]
[Pages 73739-73742]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-29317]
=======================================================================
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2013-0981; Directorate Identifier 2013-NM-032-AD]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to supersede Airworthiness Directives (ADs) 97-11-
07 and AD 99-18-23, which apply to all The Boeing Company Model MD-90-
30 airplanes. AD 97-11-07 and AD 99-18-23 currently require revising
the Airworthiness Limitations Section (ALS) of the Instructions for
Continued Airworthiness to incorporate certain compliance times for
principal structural elements (PSE) inspections and replacement times
for safe-life limited parts. Since we issued AD 97-11-07 and AD 99-18-
23, an analysis of data identified a need to introduce a new PSE
requirement for the rear spar caps of the horizontal stabilizer. This
proposed AD would require revising the maintenance or inspection
program to incorporate the new PSE requirement and its associated
inspections. We are proposing this AD to detect and correct fatigue
cracking of PSEs and certain safe-life limited parts, which could
adversely affect the structural integrity of the airplane.
DATES: We must receive comments on this proposed AD by January 23,
2014.
ADDRESSES: You may send comments, using the procedures found in 14 CFR
11.43 and 11.45, 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: Deliver to Mail address above 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, CA 90846-0001;
telephone 206-544-5000, extension 2; fax 206-766-5683; Internet https://www.myboeingfleet.com. You may view this 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 (phone: 800-647-5527) is in the ADDRESSES
section. Comments will be available in the AD docket shortly after
receipt.
FOR FURTHER INFORMATION CONTACT: Roger Durbin, Airframe Branch, ANM-
120L, FAA, Los Angeles Aircraft Certification Office (ACO), 3960
Paramount Boulevard, Lakewood, California 90712-4137; phone: (562) 627-
5233; fax: (562) 627-5210; email: roger.durbin@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-2013-0981;
Directorate Identifier 2013-NM-032-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.
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
On May 16, 1997, we issued AD 97-11-07, Amendment 39-10036 (62 FR
27941, May 22, 1997), for all The Boeing Company Model MD-90-30
airplanes. AD 97-11-07 requires revising the Airworthiness Limitations
Section of the Instructions for Continued Airworthiness (MD-90-30
Airworthiness Limitations Instructions
[[Page 73740]]
(ALI)) to add principle structural elements (PSE) requirements. AD 97-
11-07 resulted from analysis of data that identified reduced initial
inspection thresholds, reduced repetitive inspection intervals for
PSEs, and other PSEs to be added to the ALI. We issued AD 97-11-07 to
detect and correct fatigue cracking, which could result in reduced
structural integrity or reduced controllability of the airplane.
On August 27, 1999, we issued AD 99-18-23, Amendment 39-11289 (64
FR 48284, September 3, 1999), for all The Boeing Company Model MD-90-30
airplanes. AD 99-18-23 requires revising the Airworthiness Limitations
Section of the Instructions for Continued Airworthiness (MD-90-30
Airworthiness Limitations Instructions (ALI)) to incorporate certain
replacement times for safe-life limited parts. AD 99-18-23 resulted
from analysis of data that identified reduced replacement times for
certain safe-life limited parts. We issued AD 99-18-23 to prevent
fatigue cracking of various safe-life limited parts, which could
adversely affect the structural integrity of airplanes.
Actions Since Existing AD Was Issued
Since we issued AD 97-11-07, Amendment 39-10036 (62 FR 27941, May
22, 1997), and AD 99-18-23, Amendment 39-11289 (64 FR 48284, September
3, 1999), an analysis of data identified the need to introduce a new
principle structural elements (PSE) requirement for the rear spar of
the horizontal stabilizer and its associated inspections.
Relevant Service Information
We reviewed Boeing MD-90 Airworthiness Limitations Instructions
(ALI) Report No. MDC-94K9000, Revision 6, dated September 2011. For
information on the procedures and compliance times, see this service
information at https://www.regulations.gov by searching for Docket No.
FAA-2013-0981.
FAA's Determination
We are proposing this AD because we evaluated all the relevant
information and determined the unsafe condition described previously is
likely to exist or develop in other products of the same type design.
This AD requires revisions to certain operator maintenance
documents to include new actions (e.g., inspections). Compliance with
these actions is required by 14 CFR 91.403(c). For airplanes that have
been previously modified, altered, or repaired in the areas addressed
by this AD, the operator may not be able to accomplish the actions
described in the revisions. In this situation, to comply with 14 CFR
91.403(c), the operator must request approval for an alternative method
of compliance according to paragraph (n) of this proposed AD. The
request should include a description of changes to the required actions
that will ensure the continued damage tolerance of the affected
structure.
Proposed AD Requirements
This proposed AD would retain all of the requirements of AD 97-11-
07, Amendment 39-10036 (62 FR 27941, May 22, 1997), and AD 99-18-23,
Amendment 39-11289 (64 FR 48284, September 3, 1999). This proposed AD
would require revising the maintenance program to incorporate the new
PSE requirement and its associated inspections.
Costs of Compliance
We estimate that this proposed AD affects 52 airplanes of U.S.
registry.
We estimate the following costs to comply with this proposed AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost per Cost on U.S.
Action Labor cost Parts cost product operators
----------------------------------------------------------------------------------------------------------------
Revise airworthiness limitations 1 work-hour x $85 per $0 $85 $35,445
[retained actions from AD 97-11-07, hour = $85.
Amendment 39-10036 (62 FR 27941, May
22, 1997).
Revise airworthiness limitations 1 work-hour x 85 per 0 85 35,445
[retained actions from AD 99-18-23, hour = 85.
Amendment 39-11289 (64 FR 48284,
September 3, 1999).
Revise airworthiness limitations [new 1 work-hour x 85 per 0 85 35,445
proposed action]. hour = 85.
----------------------------------------------------------------------------------------------------------------
Authority for this Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, Section 106, describes the
authority of the FAA Administrator. Subtitle VII, Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701, ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We have determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect on the States, on the relationship
between the national Government and the States, or on the distribution
of power and responsibilities among the various levels of government.
For the reasons discussed above, I certify that the proposed
regulation:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979),
(3) Will not affect intrastate aviation in Alaska, and
(4) 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.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
[[Page 73741]]
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
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 FAA amends Sec. 39.13 by:
0
a. Removing airworthiness directive (AD) 97-11-07, Amendment 39-10036
(62 FR 27941, May 22, 1997), and AD 99-18-23, Amendment 39-11289 (64 FR
48284, September 3, 1999), and
0
b. Adding the following new AD:
The Boeing Company: Docket No. FAA-2013-0981; Directorate Identifier
2013-NM-032-AD.
(a) Comments Due Date
The FAA must receive comments on this AD action by January 23,
2014.
(b) Affected ADs
This AD supersedes AD 97-11-07, Amendment 39-10036 (62 FR 27941,
May 22, 1997), and AD 99-18-23, Amendment 39-11289 (64 FR 48284,
September 3, 1999).
(c) Applicability
This AD applies to all The Boeing Company Model MD-90-30
airplanes, certificated in any category.
(d) Subject
Air Transport Association (ATA) of America Code 51, Standard
Practices/Structures; Code 55, Stabilizers.
(e) Unsafe Condition
This AD was prompted by an analysis of data that identified a
need to introduce a new principal structural elements (PSE)
requirement for the rear spar caps of the horizontal stabilizer. We
are issuing this AD to detect and correct fatigue cracking of PSEs
and certain safe-life limited parts, which could adversely affect
the structural integrity of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Retained Revision of Airworthiness Limitations of Principal
Structural Elements
This paragraph restates the requirements of paragraph (a) of AD
97-11-07, Amendment 39-10036 (62 FR 27941, May 22, 1997). Within 180
days after June 26, 1997 (the effective date of AD 97-11-07,
Amendment 39-10036 (62 FR 27941, May 22, 1997)), revise the
Airworthiness Limitations Section of the Instructions for Continued
Airworthiness (Airworthiness Limitations Instructions (ALI),
McDonnell Douglas Report No. MDC-94K9000, dated November 1994) to
incorporate the Item, Location, and Inspection Interval of principal
structural elements identified in paragraphs (g)(1) through (g)(3)
of this AD. This may be accomplished by inserting a copy of Revision
1 of the ALI, dated January 1995; or a copy of this AD into the ALI.
(1) For Item 53.30.02.3 at Skin Panels, STA 237 to 1395 Fuselage
Skin in Constant Section from Longeron 3 Left to Longeron 3 Right:
Initial Interval at 60,000 landings. Repeat the inspection
thereafter at intervals not to exceed 11,000 landings.
(2) For Item 53.30.02.4 at Skin Panels, STA 237 to 1395 Fuselage
Hoop Skin Splice in Constant Section from Longeron 5 Left to
Longeron 5 Right: Initial Interval at 60,000 landings. Repeat the
inspection thereafter at intervals not to exceed 30,000 landings.
(3) For Item 54.10.04.1 at Thrust Bulkhead, Pylon--STA Yn
170.5--Rear Spar and Engine Thrust Support Fitting (Upper and
Lower): Initial Interval at 15,000 landings. Repeat the inspection
thereafter at intervals not to exceed 4,500 landings.
(h) Retained Revision of Airworthiness Limitations
(1) This paragraph restates the requirements of paragraph (b) of
AD 97-11-07, Amendment 39-10036 (62 FR 27941, May 22, 1997). Within
180 days after June 26, 1997 (the effective date of AD 97-11-07,
Amendment 39-10036 (62 FR 27941, May 22, 1997)), revise the
Airworthiness Limitations Section of the Instructions for Continued
Airworthiness (Airworthiness Limitations Instructions (ALI),
McDonnell Douglas Report No. MDC-94K9000, dated November 1994) to
incorporate the Item, Location, and Inspection Interval of principal
structural element specified in paragraph (h)(2) of this AD. This
may be accomplished by inserting a copy of Revision 2 to the ALI,
dated July 1996, or a copy this AD into the ALI or Airworthiness
Limitations Section.
(2) For Item 55.13.01.1 at Plates/Skin--Upper STA Xh 27.2 Left
to Xh 27.2 Right--Upper Aft Skin Plank with Integral Stringers from
Xh 7.234 to Xh 26.859: Initial Interval at 60,000 landings. Repeat
the inspection thereafter at intervals not to exceed 8,100 landings.
(i) Retained Restriction on Alternative Inspections and Inspection
Intervals
This paragraph restates the restriction on alternative
inspections and inspection intervals required by paragraph (c) of AD
97-11-07, Amendment 39-10036 (62 FR 27941, May 22, 1997). Except as
provided by paragraphs (l) and (n) of this AD:
After the actions required by paragraphs (g) and (h) of this AD
have been accomplished, no alternative inspections or inspection
intervals may be approved for the parts specified in paragraphs (g)
and (h) of this AD.
(j) Retained Revision of Airworthiness Limitations of Safe-Life Limited
Parts:
This paragraph restates the requirements of paragraph (a) of AD
99-18-23, Amendment 39-11289 (64 FR 48284, September 3, 1999).
Within 180 days after October 8, 1999 (the effective date of AD 99-
18-23, Amendment 39-48284 (64 FR 48284, September 3, 1999)), revise
the Airworthiness Limitations Section of the Instructions for
Continued Airworthiness (Airworthiness Limitations Instructions
(ALI), McDonnell Douglas Report No. MDC-94K9000, dated November
1994) to incorporate the Part Number, Item, and Mandatory
Replacement Time of certain safe-life limited parts by inserting a
copy of Revision 3, to the ALI, dated November 1997, into the ALI.
(k) Retained Restriction on Alternative Inspections and Inspection
Intervals
This paragraph restates the restriction on alternative
inspections and inspection intervals required by paragraph (b) of AD
99-18-23, Amendment 39-11289 (64 FR 48284, September 3, 1999).
Except as provided by paragraphs (l) and (n) of this AD: After the
actions required by paragraph (j) of this AD have been accomplished,
no alternative replacement times for the safe-life limited parts
specified in McDonnell Douglas ALI Report No. MDC-94K9000, Revision
3, dated November 1997.
(l) New Requirements of This AD: Revision of the Maintenance Program
(1) Within 180 days after the effective date of this AD, revise
the maintenance or inspection program, as applicable, to incorporate
the tasks specified in Airworthiness Limitations Instructions (ALI),
Boeing Report No. MDC-94K9000, Revision 6, dated September 2011. The
compliance times for the initial and repetitive intervals for the
tasks are stated in Airworthiness Limitations Instructions (ALI),
Boeing Report No. MDC-94K9000, Revision 6, dated September 2011.
Doing the revision required by this paragraph terminates the
revisions required by paragraphs (g), (h), and (j) of this AD.
(m) No Alternative Actions or Intervals
After accomplishing the revision required by paragraph (l) of
this AD, no alternative actions (e.g., inspections) or intervals may
be used unless the actions or intervals are approved as an
alternative method of compliance (AMOC) in accordance with the
procedures specified in paragraph (n) of this AD.
(n) Alternative Methods of Compliance (AMOCs)
(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. 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 paragraph (o) of this AD.
(2) Before using any approved AMOC, notify your appropriate
principal inspector, or lacking a principal inspector, the manager
of the local flight standards district office/certificate holding
district office.
(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 Boeing
Commercial Airplanes Organization Designation Authorization (ODA)
that has been authorized by the Manager, Los Angeles
[[Page 73742]]
ACO to make those findings. For a repair method to be approved, the
repair must meet the certification basis of the airplane and the
approval must specifically refer to this AD.
(4) AMOCs approved for AD 97-11-07, Amendment 39-10036 (62 FR
27941, May 22, 1997), and AD 99-18-23, Amendment 39-11289 (64 FR
48284, September 3, 1999), are approved as AMOCs for the
corresponding provisions of this AD.
(o) Related Information
(1) For more information about this AD, contact Roger Durbin,
Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification
Office (ACO), 3960 Paramount Boulevard, Lakewood, California 90712-
4137; phone: (562) 627-5233; fax: (562) 627-5210; email:
roger.durbin@faa.gov.
(2) For service information identified in this AD, contact
Boeing Commercial Airplanes, Attention: Data & Services Management,
3855 Lakewood Boulevard, MC D800-0019, Long Beach, CA 90846-0001;
telephone 206-544-5000, extension 2; fax 206-766-5683; Internet
https://www.myboeingfleet.com. You may view this 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.
Issued in Renton, Washington, on November 29, 2013.
John P. Piccola,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2013-29317 Filed 12-6-13; 8:45 am]
BILLING CODE 4910-13-P
