Airworthiness Directives; Cessna Aircraft Company Airplanes, 32349-32353 [2013-12662]
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Federal Register / Vol. 78, No. 104 / Thursday, May 30, 2013 / Rules and Regulations
A340–56–5002, Revision 01, including
Appendix 01, dated February 8, 2012.
(i) Credit for Previous Actions
This paragraph provides credit for the
actions required by paragraphs (g) and (h) of
this AD, if those actions were performed
before the effective date of this AD using the
applicable service information identified in
paragraphs (i)(1) through (i)(4) of this AD,
which are not incorporated by reference in
this AD.
(1) Airbus Service Bulletin A330–56–3009,
dated May 4, 2010 (for Model A330–201,
–202, –203, –223, –223F, –243, –243F, –301,
–302, –303, –321, –322, –323, –341, –342,
and –343 airplanes).
(2) Airbus Service Bulletin A330–56–3009,
Revision 01, dated January 27, 2011 (for
Model A330–201, –202, –203, –223, –223F,
–243, –243F, –301, –302, –303, –321, –322,
–323, –341, –342, and –343 airplanes).
(3) Airbus Service Bulletin A340–56–4008,
dated May 4, 2010 (for Model A340–211,
–212, –213, –311, –312, and –313 airplanes).
(4) Airbus Service Bulletin A340–56–5002,
dated May 4, 2010 (for Model A340–541 and
–642 airplanes).
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(j) Parts Installation Limitation
As of the effective date of this AD, do not
install on an airplane any affected
windshield from SGS having a part number
and serial number identified in the
applicable service information identified in
paragraphs (j)(1), (j)(2), and (j)(3) of this AD,
unless a suffix ‘‘U’’ is present at the end of
the serial number.
(1) For Model A330–201, –202, –203, –223,
–223F, –243, –243F, –301, –302, –303, –321,
–322, –323, –341, –342, and –343 airplanes:
Airbus Mandatory Service Bulletin A330–56–
3009, Revision 02, including Appendix 01,
dated February 8, 2012.
(2) For Model A340–211, –212, –213, –311,
–312, and –313 airplanes: Airbus Mandatory
Service Bulletin A340–56–4008, Revision 01,
including Appendix 01, dated February 8,
2012.
(3) For Model A340–541 and –642
airplanes: Airbus Mandatory Service Bulletin
A340–56–5002, Revision 01, including
Appendix 01, dated February 8, 2012.
(k) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Branch, ANM–116, Transport Airplane
Directorate, 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 International Branch, send it to ATTN:
Vladimir Ulyanov, Aerospace Engineer,
International Branch, ANM–116, Transport
Airplane Directorate, FAA, 1601 Lind
Avenue SW., Renton, WA 98057–3356;
telephone (425) 227–1138; fax (425) 227–
1149. Information may be emailed to: 9ANM-116-AMOC-REQUESTS@faa.gov.
Before using any approved AMOC, notify
your appropriate principal inspector, or
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lacking a principal inspector, the manager of
the local flight standards district office/
certificate holding district office. The AMOC
approval letter must specifically reference
this AD.
(2) Airworthy Product: For any requirement
in this AD to obtain corrective actions from
a manufacturer or other source, use these
actions if they are FAA-approved. Corrective
actions are considered FAA-approved if they
are approved by the State of Design Authority
(or their delegated agent). You are required
to assure the product is airworthy before it
is returned to service.
(5) You may view this service information
that is incorporated by reference 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/ibrlocations.html.
(l) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information European
Aviation Safety Agency Airworthiness
Directive 2011–0242, dated December 19,
2011 (corrected February 15, 2012), and the
service information identified in paragraphs
(l)(1)(i) through (l)(1)(iii) of this AD, for
related information.
(i) Airbus Mandatory Service Bulletin
A330–56–3009, Revision 02, including
Appendix 01, dated February 8, 2012.
(ii) Airbus Mandatory Service Bulletin
A340–56–4008, Revision 01, including
Appendix 01, dated February 8, 2012.
(iii) Airbus Mandatory Service Bulletin
A340–56–5002, Revision 01, including
Appendix 01, dated February 8, 2012.
(2) For service information identified in
this AD, contact Airbus SAS—Airworthiness
Office—EAL, 1 Rond Point Maurice Bellonte,
31707 Blagnac Cedex, France; telephone +33
5 61 93 36 96; fax +33 5 61 93 45 80; email
airworthiness.A330-A340@airbus.com;
Internet https://www.airbus.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.
[FR Doc. 2013–12519 Filed 5–29–13; 8:45 am]
(m) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless the AD specifies otherwise.
(i) Airbus Mandatory Service Bulletin
A330–56–3009, Revision 02, including
Appendix 01, dated February 8, 2012.
(ii) Airbus Mandatory Service Bulletin
A340–56–4008, Revision 01, including
Appendix 01, dated February 8, 2012.
(iii) Airbus Mandatory Service Bulletin
A340–56–5002, Revision 01, including
Appendix 01, dated February 8, 2012.
(3) For service information identified in
this AD, contact Airbus SAS—Airworthiness
Office—EAL, 1 Rond Point Maurice Bellonte,
31707 Blagnac Cedex, France; telephone +33
5 61 93 36 96; fax +33 5 61 93 45 80; email
airworthiness.A330-A340@airbus.com;
Internet https://www.airbus.com.
(4) You may review copies of the 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.
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Issued in Renton, Washington, on May 16,
2013.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2012–1001; Directorate
Identifier 2012–NM–020–AD; Amendment
39–17453; AD 2013–09–11]
RIN 2120–AA64
Airworthiness Directives; Cessna
Aircraft Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for certain
Cessna Aircraft Company Model 500,
501, 550, 551, S550, 560, 560XL, and
650 airplanes. This AD was prompted
by multiple reports of smoke and/or fire
in the tailcone caused by sparking due
to excessive wear of the brushes in the
air conditioning (A/C) motor. This AD
requires inspecting to determine if
certain A/C compressor motors are
installed and to determine the
accumulated hours on certain A/C drive
motor assemblies; repetitive
replacement of the brushes in the drive
motor assembly, or, as an option to the
brush replacement, deactivation of the
A/C system and placard installation;
and return of replaced brushes to
Cessna. We are issuing this AD to
prevent the brushes in the A/C motor
from wearing down beyond their limits,
which could result in the rivet in the
brush contacting the commutator
causing sparks and consequent fire and/
or smoke in the tailcone with no means
to detect or extinguish the fire and/or
smoke.
DATES: This AD is effective July 5, 2013.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in the AD
as of July 5, 2013.
ADDRESSES: For service information
identified in this AD, contact Cessna
SUMMARY:
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Federal Register / Vol. 78, No. 104 / Thursday, May 30, 2013 / Rules and Regulations
Aircraft Co., P.O. Box 7706, Wichita, KS
67277; telephone 316–517–6215; fax
316–517–5802; email
citationpubs@cessna.textron.com;
Internet https://
www.cessnasupport.com/newlogin.html.
You may review copies of the
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 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 (phone: 800–647–5527) is
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:
Christine Abraham, Aerospace Engineer,
Electrical Systems and Avionics Branch,
ACE–119W, FAA, Wichita Aircraft
Certification Office (ACO), 1801 Airport
Road, Room 100, Mid-Continent
Airport, Wichita, Kansas 67209; phone:
316–946–4165; fax: 316–946–4107;
email: wichita-cos@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a supplemental notice of
proposed rulemaking (SNPRM) to
amend 14 CFR part 39 to include an
airworthiness directive (AD) that would
apply to the specified products. That
SNPRM published in the Federal
Register on February 11, 2013 (78 FR
9636). The original NPRM (77 FR 59146,
September 26, 2012) proposed to require
an inspection to determine if certain
A/C compressor motors are installed
and to determine the accumulated hours
on certain A/C drive motor assemblies;
repetitive replacement of the brushes in
the drive motor assembly, or, as an
option to the brush replacement,
deactivation of the A/C system and
placard installation; and return of
replaced brushes to Cessna. The SNPRM
proposed to revise the optional A/C
system deactivation procedure.
Comments
We gave the public the opportunity to
participate in developing this AD. We
received no comments on the SNPRM
(78 FR 9636, February 11, 2013) or on
the determination of the cost to the
public.
Conclusion
We reviewed the relevant data and
determined that air safety and the
public interest require adopting the AD
as proposed—except for minor editorial
changes. We have determined that these
minor changes:
• Are consistent with the intent that
was proposed in the SNPRM (78 FR
9636, February 11, 2013) for correcting
the unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the SNPRM (78 FR 9636,
February 11, 2013).
Interim Action
We consider this AD interim action.
The reporting data required by this AD
will enable us to obtain better insight
into brush wear. The reporting data will
also indicate if the replacement
intervals we established are adequate.
After we analyze the reporting data
received, we might consider further
rulemaking.
Model 525 airplanes are not subject to
this AD. We are currently considering
requiring similar actions for these
airplanes.
Costs of Compliance
We estimate that this AD will affect
1,987 airplanes of U.S. registry.
We estimate the following costs to
comply with this AD:
ESTIMATED COSTS
Cost per
product
Cost on U.S.
operators
Action
Labor cost
Parts cost
Inspection, drive motor assembly brush replacement, parts return, and reporting.
11 work-hours × $85
per hour = $935 per
replacement cycle.
1 work-hour × $85 per
hour = $85.
1 work-hour × $85 per
hour = $85.
$252 per replacement
cycle.
$1,187 per replacement cycle.
$2,358,569 per replacement cycle.
$0 ...............................
$85 .............................
$168,895.
$0 ...............................
$85 .............................
$31,450.
Optional fabrication of placard for deactivation.
Optional deactivation or reactivation for
Model 560XL airplanes (370 airplanes).
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Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
section 106, describes the authority of
the FAA Administrator. Subtitle VII:
Aviation Programs, describes in more
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in Subtitle VII,
Part A, Subpart III, Section 44701:
‘‘General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
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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
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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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),
(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.
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Federal Register / Vol. 78, No. 104 / Thursday, May 30, 2013 / 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:
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 airworthiness
directive (AD):
■
2013–09–11 Cessna Aircraft Company:
Amendment 39–17453; Docket No.
FAA–2012–1001; Directorate Identifier
2012–NM–020–AD.
(a) Effective Date
This AD is effective July 5, 2013.
(b) Affected ADs
None.
(c) Applicability
This AD applies to the following Cessna
Aircraft Company airplanes, certificated in
any category.
(1) Model 500 and 501 airplanes, serial
numbers (S/N) 0001 through 0689 inclusive.
(2) Model 550 and 551 airplanes, S/Ns
0002 through 0733 inclusive, and 0801
through 1136 inclusive.
(3) Model S550 airplanes, S/Ns 0001
through 0160 inclusive.
(4) Model 560 airplanes, S/Ns 0001
through 0707 inclusive, and 0751 through
0815 inclusive.
(5) Model 560XL airplanes, S/Ns 5001
through 5300 inclusive.
(6) Model 650 airplanes, S/Ns 0200
through 0241 inclusive, and 7001 through
7119 inclusive.
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(d) Subject
Joint Aircraft System Component (JASC)/
Air Transport Association (ATA) of America
Code 21, Air Conditioning.
(e) Unsafe Condition
This AD was prompted by multiple reports
of smoke and/or fire in the tailcone caused
by sparking due to excessive wear of the
brushes in the air conditioning (A/C) motor.
We are issuing this AD to prevent the brushes
in the A/C motor from wearing down, which
could result in the rivet in the brush
contacting the commutator causing sparks
and consequent fire and/or smoke in the
tailcone with no means to detect or
extinguish the fire and/or smoke.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
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(g) Inspection for Part Number (P/N)
Within 30 days or 10 flight hours after the
effective date of this AD, whichever occurs
first: Inspect the A/C compressor motor to
determine whether P/N 1134104–1 or P/N
1134104–5 is installed. A review of airplane
maintenance records is acceptable in lieu of
this inspection if the part number of the
A/C compressor motor can be conclusively
determined from that review.
(h) Inspection of Compressor Hour Meter
and Maintenance Records
If, during the inspection required by
paragraph (g) of this AD, any A/C compressor
motor is found having P/N 1134104–1 or
P/N 1134104–5: Within 30 days or 10 flight
hours after the effective date of this AD,
whichever occurs first, determine the hour
reading on the A/C compressor hour meter as
specified in paragraphs (h)(1) and (h)(2) of
this AD.
(1) Inspect the number of hours on the
A/C compressor hour meter. And,
(2) Check the airplane logbook for any
entry for replacing the A/C compressor motor
brushes with new brushes, or for replacing
the compressor motor or compressor
condenser module assembly (pallet) with a
motor or assembly that has new brushes.
(i) If the logbook contains an entry for
replacement of parts, as specified in
paragraph (h)(2) of this AD, determine the
number of hours on the A/C compressor
motor brushes by comparing the number of
hours on the compressor motor since
replacement and use this number in lieu of
the number determined in paragraph (h)(1) of
this AD. Or,
(ii) If, through the logbook check you
cannot positively determine the number of
hours on the A/C compressor motor brushes,
as specified in paragraph (h)(2) of this AD,
use the number of hours on the A/C
compressor hour meter determined in
paragraph (h)(1) of this AD or presume the
brushes have over 500 hours time-in-service.
(i) Replacement
Using the hour reading on the A/C
compressor hour meter determined in
paragraph (h) of this AD, replace the A/C
compressor motor brushes with new brushes
at the later of the times specified in
paragraphs (i)(1) and (i)(2) of this AD.
Thereafter, repeat the replacement of the
A/C compressor motor brushes at intervals
not to exceed 500 hours time-in-service on
the A/C compressor motor. Do the
replacement in accordance with the
applicable Cessna maintenance manual
subject specified in paragraphs (j)(1) through
(j)(7) of this AD.
(1) Before the accumulation of 500 total
hours time-in-service on the A/C compressor
motor.
(2) Before further flight after doing the
inspection required in paragraph (h) of this
AD.
(j) Replacement Maintenance Manual
Information
Use the instructions in the applicable
Cessna maintenance manual subject specified
in paragraphs (j)(1) through (j)(7) of this AD
to do the replacement required by paragraph
(i) of this AD.
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(1) Subject 4–11–00, Replacement Time
Limits, of Chapter 4, Airworthiness
Limitations, Revision 10, dated April 23,
2012, of the Cessna Model 550 Bravo
Maintenance Manual.
(2) Subject 4–11–00, Replacement Time
Limits, of Chapter 4, Airworthiness
Limitations, Revision 8, dated April 23, 2012,
of the Cessna Model 550Maintenance
Manual.
(3) Subject 4–11–00, Replacement Time
Limits, of Chapter 4, Airworthiness
Limitations, Revision 20, dated April 23,
2012, of the Cessna Model 560 Maintenance
Manual.
(4) Subject 4–11–00, Replacement Time
Limits, of Chapter 4, Airworthiness
Limitations, Revision 13, dated April 23,
2012, of the Cessna Model
560XLMaintenance Manual.
(5) Subject 4–11–00, Replacement Time
Limits, of Chapter 4, Airworthiness
Limitations, Revision 30, dated April 23,
2012, of the Cessna Model 650 Maintenance
Manual.
(6) Subject 4–11–00, Replacement Time
Limits-General, of Chapter 4, Airworthiness
Limitations, Revision 4, dated April 23, 2012,
of the Cessna Model 500/501Maintenance
Manual.
(7) Subject 4–11–00, Replacement Time
Limits, of Chapter 4, Airworthiness
Limitations, Revision 7, dated April 23, 2012,
of the Cessna Model S550 Maintenance
Manual.
(k) Deactivation of A/C System
In lieu of replacing the A/C compressor
motor brushes as required by this AD,
deactivate the A/C system as specified in
paragraph (k)(1), (k)(2), or (k)(3) of this AD,
as applicable.
(1) For all airplanes except Model 560XL
and 650 airplanes: Pull the vapor cycle A/C
circuit breaker labeled ‘‘AIR COND,’’ do the
actions specified in paragraphs (k)(1)(i) and
(k)(1)(ii) of this AD, and document
deactivation of the system in the airplane
logbook, referring to this AD as the reason for
deactivation. While the system is
deactivated, the airplane operator must
remain aware of operating temperature
limitations specified in the applicable
airplane flight manual.
(i) Fabricate a placard that states: ‘‘A/C
DISABLED’’ with 1⁄8-inch black lettering on
a white background.
(ii) Install the placard on the airplane
instrument panel within 6 inches of the
A/C selection switch.
(2) For Model 650 airplanes: Pull the vapor
cycle A/C circuit breaker labeled ‘‘FWD
EVAP FAN,’’ do the actions specified in
paragraphs (k)(1)(i) and (k)(1)(ii) of this AD,
and document deactivation of the system in
the airplane logbook, referring to this AD as
the reason for deactivation. While the system
is deactivated, the airplane operator must
remain aware of operating temperature
limitations specified in the applicable
airplane flight manual.
(3) For Model 560XL airplanes: Do the
actions specified in paragraphs (k)(1)(i) and
(k)(1)(ii) of this AD, and document
deactivation of the system in the airplane
logbook, referring to this AD as the reason for
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deactivation. While the system is
deactivated, the airplane operator must
remain aware of operating temperature
limitations specified in the applicable
airplane flight manual. Remove the fuse
limiter that supplies power to the A/C
compressor motor by doing the actions
specified in paragraphs (k)(3)(i) through
(k)(3)(viii) of this AD, and return to the
airplane to service by doing the actions
specified in paragraphs (k)(3)(ix) through
(k)(3)(xiii) of this AD.
(i) Open the battery door.
(ii) Disconnect the main battery connector
and remove external electrical power.
(iii) Tag the battery and external power
receptacle with a warning tag that reads:
‘‘WARNING: Do not connect the battery
connector during the maintenance in
progress.’’
(iv) Gain access to the J-Box through the
tailcone access door.
(v) Remove the wing nuts that attach the
cover to the J-Box.
(vi) Remove the J-Box cover.
(vii) Remove nuts securing compressor fuse
limiter (reference designator HZ116, P/N
ANL130) to the bus bar.
(viii) Remove the compressor motor fuse
limiter from the terminals and retain for
future reinstallation once the compressor
motor brushes have been replaced.
(ix) Install fuse limiter nuts on the
terminals and torque to 100 inch-pounds
+/– 5 inch-pounds.
(x) Install the J-Box cover with wing nuts.
(xi) Remove the warning tag on the battery
and external power receptacle.
(xii) Connect the battery and restore
electrical power to the airplane.
(xiii) Close the tailcone access door.
(l) Reactivation of A/C System
If an operator chooses to deactivate the
A/C system, as specified in paragraph (k) of
this AD, and then later chooses to return the
A/C system to service: Before returning the
A/C system to service and removing the
placard, perform the inspection specified in
paragraph (h) of this AD, and do the
replacements specified in paragraph (i) of
this AD, at the times specified in paragraph
(i) of this AD. Return the A/C system to
service by doing the actions specified in
paragraph (l)(1), (l)(2), or (l)(3) of this AD, as
applicable.
(1) For all airplanes except Model 560XL
and 650 airplanes: Push in the vapor cycle
A/C circuit breaker labeled ‘‘AIR COND,’’
remove the placard by the A/C selection
switch that states ‘‘A/C DISABLED,’’ and
document reactivation of the system in the
airplane logbook.
(2) For Model 650 airplanes: Push in the
vapor cycle A/C circuit breaker labeled
‘‘FWD EVAP FAN,’’ remove the placard by
the A/C selection switch that states ‘‘A/C
DISABLED,’’ and document reactivation of
the system in the airplane logbook.
(3) For Model 560XL airplanes: Remove the
placard by the A/C selection switch that
states ‘‘A/C DISABLED,’’ and document
reactivation of the system in the airplane
logbook. Re-install the fuse limiter by doing
the actions specified in paragraphs (l)(3)(i)
through (l)(3)(viii) of this AD, and return to
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the airplane to service by doing the actions
specified in paragraphs (l)(3)(ix) through
(l)(3)(xiii) of this AD.
(i) Open the battery door.
(ii) Disconnect the main battery connector
and remove external electrical power.
(iii) Tag the battery and external power
receptacle with a warning tag that reads:
‘‘WARNING: Do not connect the battery
connector during the maintenance in
progress.’’
(iv) Gain access to the J-Box through the
tailcone access door.
(v) Remove the wing nuts that attach the
cover to the J-Box.
(vi) Remove the J-Box cover.
(vii) Remove the fuse limiter nuts on the
bus bar terminals for the fuse limiter.
(viii) Install the compressor motor fuse
limiter (reference designator HZ116, P/N
ANL130).
(ix) Install fuse limiter nuts on the
terminals and torque to 100 inch-pounds
+/– 5 inch-pounds.
(x) Install the J-Box cover with wing nuts.
(xi) Remove the warning tag on the battery
and external power receptacle.
(xii) Connect the battery and restore
electrical power to the airplane.
(xiii) Close the tailcone access door.
(m) Parts Return and Reporting
Requirements
For the first two A/C compressor motor
brush replacement cycles on each airplane,
send the brushes that were removed to
Cessna Aircraft Company, Cessna Service
Parts and Programs, 7121 Southwest
Boulevard, Wichita, KS 67215. Provide the
brushes and the information specified in
paragraphs (m)(1) through (m)(6) of this AD
within 30 days after the replacement, if the
replacement was done on or after the
effective date of this AD, or within 30 days
after the effective date of this AD, if the
replacement was done before the effective
date of this AD.
(1) The model and serial number of the
airplane.
(2) The part number of the motor.
(3) The part number of the brushes, if
known.
(4) The elapsed amount of motor hours
since the last brush/motor replacement, if
known.
(5) If motor hours are unknown, report the
elapsed airplane flight hours since the last
brush/motor replacement and indicate that
motor hours are unknown.
(6) The number of motor hours currently
displayed on the pallet hour meter.
(n) Parts Installation Limitation
As of the effective date of this AD, no
person may install an A/C compressor motor
having P/N 1134104–1 or P/N 1134104–5,
unless the inspection specified in paragraph
(h) of this AD is done before further flight,
and the replacements specified in paragraph
(i) of this AD are done at the times specified
in paragraph (i) of this AD.
(o) Special Flight Permit Limitation
Operation of the A/C system is prohibited
while flying with a special flight permit
issued for this AD.
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(p) Paperwork Reduction Act Burden
Statement
A federal agency may not conduct or
sponsor, and a person is not required to
respond to, nor shall a person be subject to
a penalty for failure to comply with a
collection of information subject to the
requirements of the Paperwork Reduction
Act unless that collection of information
displays a current valid OMB Control
Number. The OMB Control Number for this
information collection is 2120–0056. Public
reporting for this collection of information is
estimated to be approximately 5 minutes per
response, including the time for reviewing
instructions, completing and reviewing the
collection of information. All responses to
this collection of information are mandatory.
Comments concerning the accuracy of this
burden and suggestions for reducing the
burden should be directed to the FAA at: 800
Independence Ave. SW., Washington, DC
20591, Attn: Information Collection
Clearance Officer, AES–200.
(q) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Wichita 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 the
Related Information section 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.
(r) Related Information
For more information about this AD,
contact Christine Abraham, Aerospace
Engineer, Electrical Systems and Avionics
Branch, ACE–119W, FAA, Wichita Aircraft
Certification Office (ACO), 1801 Airport
Road, Room 100, Mid-Continent Airport,
Wichita, Kansas 67209; phone: 316–946–
4165; fax: 316–946–4107; email: wichitacos@faa.gov.
(s) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless the AD specifies otherwise.
(i) Subject 4–11–00, Replacement Time
Limits, of Chapter 4, Airworthiness
Limitations, Revision 10, dated April 23,
2012, of the Cessna Model 550 Bravo
Maintenance Manual. The revision level of
Chapter 4 is identified only on the title page
of Chapter 4.
(ii) Subject 4–11–00, Replacement Time
Limits, of Chapter 4, Airworthiness
Limitations, Revision 8, dated April 23, 2012,
of the Cessna Model 550 Maintenance
Manual. The revision level of Chapter 4 is
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Federal Register / Vol. 78, No. 104 / Thursday, May 30, 2013 / Rules and Regulations
rmajette on DSK2TPTVN1PROD with RULES
identified only on the title page of Chapter
4.
(iii) Subject 4–11–00, Replacement Time
Limits, of Chapter 4, Airworthiness
Limitations, Revision 20, dated April 23,
2012, of the Cessna Model 560 Maintenance
Manual. The revision level of Chapter 4 is
identified only on the title page of Chapter
4.
(iv) Subject 4–11–00, Replacement Time
Limits, of Chapter 4, Airworthiness
Limitations, Revision 13, dated April 23,
2012, of the Cessna Model 560XL
Maintenance Manual. The revision level of
Chapter 4 is identified only on the title page
of Chapter 4.
(v) Subject 4–11–00, Replacement Time
Limits, of Chapter 4, Airworthiness
Limitations, Revision 30, dated April 23,
2012, of the Cessna Model 650 Maintenance
Manual. The revision level of Chapter 4 is
identified only on the title page of Chapter
4.
(vi) Subject 4–11–00, Replacement Time
Limits-General, of Chapter 4, Airworthiness
Limitations, Revision 4, dated April 23, 2012,
of the Cessna Model 500/501Maintenance
Manual. The revision level of Chapter 4 is
identified only on the title page of Chapter
4.
(vii) Subject 4–11–00, Replacement Time
Limits, of Chapter 4, Airworthiness
Limitations, Revision 7, dated April 23, 2012,
of the Cessna Model S550 Maintenance
Manual. The revision level of Chapter 4 is
identified only on the title page of Chapter
4.
(3) For Cessna service information
identified in this AD, contact Cessna Aircraft
Co., P.O. Box 7706, Wichita, KS 67277;
telephone 316–517–6215; fax 316–517–5802;
email citationpubs@cessna.textron.com;
Internet https://www.cessnasupport.com/
newlogin.html.
(4) You may view this service information
at 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.
(5) You may view this service information
that is incorporated by reference 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/ibrlocations.html.
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2013–0426; Directorate
Identifier 2013–NM–084–AD; Amendment
39–17463; AD 2013–11–03]
RIN 2120–AA64
Airworthiness Directives; Bombardier,
Inc. Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final Rule; Request for
Comments.
AGENCY:
Issued in Renton, Washington, on April 26,
2013.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
We are adopting a new
airworthiness directive (AD) for certain
Bombardier, Inc. Model CL–215–1A10
and CL–215–6B11 (CL–215T Variant)
airplanes. This AD requires repetitive
detailed inspections for cracking of the
left-hand (LH) and right-hand (RH) wing
lower skin, and repair if necessary. This
AD also provides terminating action for
the repetitive detailed inspections. This
AD was prompted by reports of a
fractured wing lower rear spar cap and
reinforcing strap. We are issuing this AD
to detect and correct cracked wing
structure, which could result in failure
of the wing.
DATES: This AD becomes effective June
14, 2013.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in the AD
as of June 14, 2013.
We must receive comments on this
AD by July 15, 2013.
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.
[FR Doc. 2013–12662 Filed 5–29–13; 8:45 am]
Examining the AD Docket
BILLING CODE 4910–13–P
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,
VerDate Mar<15>2010
14:56 May 29, 2013
Jkt 229001
SUMMARY:
PO 00000
Frm 00009
Fmt 4700
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32353
except Federal holidays. The AD docket
contains this 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:
Ricardo Garcia, Aerospace Engineer,
Airframe and Mechanical Systems
Branch, ANE–171, FAA, New York
Aircraft Certification Office (ACO), 1600
Stewart Avenue, Suite 410, Westbury,
New York 11590; telephone (516) 228–
7331; fax (516) 794–5531.
SUPPLEMENTARY INFORMATION:
Discussion
Transport Canada Civil Aviation
(TCCA), which is the aviation authority
for Canada, has issued Emergency
Canadian Airworthiness Directive CF–
2013–11, dated April 17, 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:
While performing modifications on a CL–
215–1A10 aeroplane, an operator discovered
that the wing lower rear spar cap and
reinforcing strap were fractured at Wing
Stations (WS) 49.5 and 50 respectively and
the rear spar web and wing lower skin were
also cracked. It is suspected that a crack
initiated at the wing lower spar cap, leading
to its failure, the subsequent failure of the
reinforcing strap and cracking of the spar
web and wing lower skin. The damage was
outside of the area addressed by the
repetitive ultrasonic inspections required by
AD CF–1992–26R2 [which corresponds to
FAA AD 2012–11–04, Amendment 39–17067
(77 FR 32892, June 4, 2012)] and was found
95 hours air time after the last ultrasonic
inspection.
Failure and cracking of the above-noted
wing structure, if not detected, could result
in failure of the wing. In order to mitigate the
unsafe condition, this [Canadian] AD
mandates a repetitive [detailed] visual
inspection [for cracking] of the wing lower
skin until an eddy current inspection [for
cracking] of the [LH and RH wing lower front
and rear] spar cap[s] is performed or a
[detailed] visual inspection [for cracking] of
the wing structures [i.e., the LH and RH wing
lower skin, front and rear spar caps, front and
rear spar webs, and reinforcing straps] is
performed by removing the fuel bladder[, and
repair if any cracking is found during any
inspection]. Transport Canada may mandate
additional corrective actions pending the
outcome of the failure investigation and fleet
findings. The requirements of AD CF–1992–
26R2 remain applicable.
The terminating action is doing either a
detailed inspection for cracking of the
LH and RH wing lower skin, front and
rear spar caps, front and rear spar webs,
E:\FR\FM\30MYR1.SGM
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]]>Agencies
[Federal Register Volume 78, Number 104 (Thursday, May 30, 2013)]
[Rules and Regulations]
[Pages 32349-32353]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-12662]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2012-1001; Directorate Identifier 2012-NM-020-AD;
Amendment 39-17453; AD 2013-09-11]
RIN 2120-AA64
Airworthiness Directives; Cessna Aircraft Company Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new airworthiness directive (AD) for certain
Cessna Aircraft Company Model 500, 501, 550, 551, S550, 560, 560XL, and
650 airplanes. This AD was prompted by multiple reports of smoke and/or
fire in the tailcone caused by sparking due to excessive wear of the
brushes in the air conditioning (A/C) motor. This AD requires
inspecting to determine if certain A/C compressor motors are installed
and to determine the accumulated hours on certain A/C drive motor
assemblies; repetitive replacement of the brushes in the drive motor
assembly, or, as an option to the brush replacement, deactivation of
the A/C system and placard installation; and return of replaced brushes
to Cessna. We are issuing this AD to prevent the brushes in the A/C
motor from wearing down beyond their limits, which could result in the
rivet in the brush contacting the commutator causing sparks and
consequent fire and/or smoke in the tailcone with no means to detect or
extinguish the fire and/or smoke.
DATES: This AD is effective July 5, 2013.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in the AD as of July 5, 2013.
ADDRESSES: For service information identified in this AD, contact
Cessna
[[Page 32350]]
Aircraft Co., P.O. Box 7706, Wichita, KS 67277; telephone 316-517-6215;
fax 316-517-5802; email citationpubs@cessna.textron.com; Internet
https://www.cessnasupport.com/newlogin.html. You may review copies of
the 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 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 (phone: 800-647-5527) is 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: Christine Abraham, Aerospace Engineer,
Electrical Systems and Avionics Branch, ACE-119W, FAA, Wichita Aircraft
Certification Office (ACO), 1801 Airport Road, Room 100, Mid-Continent
Airport, Wichita, Kansas 67209; phone: 316-946-4165; fax: 316-946-4107;
email: wichita-cos@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a supplemental notice of proposed rulemaking (SNPRM) to
amend 14 CFR part 39 to include an airworthiness directive (AD) that
would apply to the specified products. That SNPRM published in the
Federal Register on February 11, 2013 (78 FR 9636). The original NPRM
(77 FR 59146, September 26, 2012) proposed to require an inspection to
determine if certain A/C compressor motors are installed and to
determine the accumulated hours on certain A/C drive motor assemblies;
repetitive replacement of the brushes in the drive motor assembly, or,
as an option to the brush replacement, deactivation of the A/C system
and placard installation; and return of replaced brushes to Cessna. The
SNPRM proposed to revise the optional A/C system deactivation
procedure.
Comments
We gave the public the opportunity to participate in developing
this AD. We received no comments on the SNPRM (78 FR 9636, February 11,
2013) or on the determination of the cost to the public.
Conclusion
We reviewed the relevant data and determined that air safety and
the public interest require adopting the AD as proposed--except for
minor editorial changes. We have determined that these minor changes:
Are consistent with the intent that was proposed in the
SNPRM (78 FR 9636, February 11, 2013) for correcting the unsafe
condition; and
Do not add any additional burden upon the public than was
already proposed in the SNPRM (78 FR 9636, February 11, 2013).
Interim Action
We consider this AD interim action. The reporting data required by
this AD will enable us to obtain better insight into brush wear. The
reporting data will also indicate if the replacement intervals we
established are adequate. After we analyze the reporting data received,
we might consider further rulemaking.
Model 525 airplanes are not subject to this AD. We are currently
considering requiring similar actions for these airplanes.
Costs of Compliance
We estimate that this AD will affect 1,987 airplanes of U.S.
registry.
We estimate the following costs to comply with this AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost on U.S.
Action Labor cost Parts cost Cost per product operators
----------------------------------------------------------------------------------------------------------------
Inspection, drive motor assembly 11 work-hours x $252 per $1,187 per $2,358,569 per
brush replacement, parts $85 per hour = replacement cycle. replacement cycle. replacement
return, and reporting. $935 per cycle.
replacement cycle.
Optional fabrication of placard 1 work-hour x $85 $0................ $85............... $168,895.
for deactivation. per hour = $85.
Optional deactivation or 1 work-hour x $85 $0................ $85............... $31,450.
reactivation for Model 560XL per hour = $85.
airplanes (370 airplanes).
----------------------------------------------------------------------------------------------------------------
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
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),
(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.
[[Page 32351]]
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:
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 adding the following new airworthiness
directive (AD):
2013-09-11 Cessna Aircraft Company: Amendment 39-17453; Docket No.
FAA-2012-1001; Directorate Identifier 2012-NM-020-AD.
(a) Effective Date
This AD is effective July 5, 2013.
(b) Affected ADs
None.
(c) Applicability
This AD applies to the following Cessna Aircraft Company
airplanes, certificated in any category.
(1) Model 500 and 501 airplanes, serial numbers (S/N) 0001
through 0689 inclusive.
(2) Model 550 and 551 airplanes, S/Ns 0002 through 0733
inclusive, and 0801 through 1136 inclusive.
(3) Model S550 airplanes, S/Ns 0001 through 0160 inclusive.
(4) Model 560 airplanes, S/Ns 0001 through 0707 inclusive, and
0751 through 0815 inclusive.
(5) Model 560XL airplanes, S/Ns 5001 through 5300 inclusive.
(6) Model 650 airplanes, S/Ns 0200 through 0241 inclusive, and
7001 through 7119 inclusive.
(d) Subject
Joint Aircraft System Component (JASC)/Air Transport Association
(ATA) of America Code 21, Air Conditioning.
(e) Unsafe Condition
This AD was prompted by multiple reports of smoke and/or fire in
the tailcone caused by sparking due to excessive wear of the brushes
in the air conditioning (A/C) motor. We are issuing this AD to
prevent the brushes in the A/C motor from wearing down, which could
result in the rivet in the brush contacting the commutator causing
sparks and consequent fire and/or smoke in the tailcone with no
means to detect or extinguish the fire and/or smoke.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Inspection for Part Number (P/N)
Within 30 days or 10 flight hours after the effective date of
this AD, whichever occurs first: Inspect the A/C compressor motor to
determine whether P/N 1134104-1 or P/N 1134104-5 is installed. A
review of airplane maintenance records is acceptable in lieu of this
inspection if the part number of the A/C compressor motor can be
conclusively determined from that review.
(h) Inspection of Compressor Hour Meter and Maintenance Records
If, during the inspection required by paragraph (g) of this AD,
any A/C compressor motor is found having P/N 1134104-1 or P/N
1134104-5: Within 30 days or 10 flight hours after the effective
date of this AD, whichever occurs first, determine the hour reading
on the A/C compressor hour meter as specified in paragraphs (h)(1)
and (h)(2) of this AD.
(1) Inspect the number of hours on the A/C compressor hour
meter. And,
(2) Check the airplane logbook for any entry for replacing the
A/C compressor motor brushes with new brushes, or for replacing the
compressor motor or compressor condenser module assembly (pallet)
with a motor or assembly that has new brushes.
(i) If the logbook contains an entry for replacement of parts,
as specified in paragraph (h)(2) of this AD, determine the number of
hours on the A/C compressor motor brushes by comparing the number of
hours on the compressor motor since replacement and use this number
in lieu of the number determined in paragraph (h)(1) of this AD. Or,
(ii) If, through the logbook check you cannot positively
determine the number of hours on the A/C compressor motor brushes,
as specified in paragraph (h)(2) of this AD, use the number of hours
on the A/C compressor hour meter determined in paragraph (h)(1) of
this AD or presume the brushes have over 500 hours time-in-service.
(i) Replacement
Using the hour reading on the A/C compressor hour meter
determined in paragraph (h) of this AD, replace the A/C compressor
motor brushes with new brushes at the later of the times specified
in paragraphs (i)(1) and (i)(2) of this AD. Thereafter, repeat the
replacement of the A/C compressor motor brushes at intervals not to
exceed 500 hours time-in-service on the A/C compressor motor. Do the
replacement in accordance with the applicable Cessna maintenance
manual subject specified in paragraphs (j)(1) through (j)(7) of this
AD.
(1) Before the accumulation of 500 total hours time-in-service
on the A/C compressor motor.
(2) Before further flight after doing the inspection required in
paragraph (h) of this AD.
(j) Replacement Maintenance Manual Information
Use the instructions in the applicable Cessna maintenance manual
subject specified in paragraphs (j)(1) through (j)(7) of this AD to
do the replacement required by paragraph (i) of this AD.
(1) Subject 4-11-00, Replacement Time Limits, of Chapter 4,
Airworthiness Limitations, Revision 10, dated April 23, 2012, of the
Cessna Model 550 Bravo Maintenance Manual.
(2) Subject 4-11-00, Replacement Time Limits, of Chapter 4,
Airworthiness Limitations, Revision 8, dated April 23, 2012, of the
Cessna Model 550Maintenance Manual.
(3) Subject 4-11-00, Replacement Time Limits, of Chapter 4,
Airworthiness Limitations, Revision 20, dated April 23, 2012, of the
Cessna Model 560 Maintenance Manual.
(4) Subject 4-11-00, Replacement Time Limits, of Chapter 4,
Airworthiness Limitations, Revision 13, dated April 23, 2012, of the
Cessna Model 560XLMaintenance Manual.
(5) Subject 4-11-00, Replacement Time Limits, of Chapter 4,
Airworthiness Limitations, Revision 30, dated April 23, 2012, of the
Cessna Model 650 Maintenance Manual.
(6) Subject 4-11-00, Replacement Time Limits-General, of Chapter
4, Airworthiness Limitations, Revision 4, dated April 23, 2012, of
the Cessna Model 500/501Maintenance Manual.
(7) Subject 4-11-00, Replacement Time Limits, of Chapter 4,
Airworthiness Limitations, Revision 7, dated April 23, 2012, of the
Cessna Model S550 Maintenance Manual.
(k) Deactivation of A/C System
In lieu of replacing the A/C compressor motor brushes as
required by this AD, deactivate the A/C system as specified in
paragraph (k)(1), (k)(2), or (k)(3) of this AD, as applicable.
(1) For all airplanes except Model 560XL and 650 airplanes: Pull
the vapor cycle A/C circuit breaker labeled ``AIR COND,'' do the
actions specified in paragraphs (k)(1)(i) and (k)(1)(ii) of this AD,
and document deactivation of the system in the airplane logbook,
referring to this AD as the reason for deactivation. While the
system is deactivated, the airplane operator must remain aware of
operating temperature limitations specified in the applicable
airplane flight manual.
(i) Fabricate a placard that states: ``A/C DISABLED'' with \1/
8\-inch black lettering on a white background.
(ii) Install the placard on the airplane instrument panel within
6 inches of the A/C selection switch.
(2) For Model 650 airplanes: Pull the vapor cycle A/C circuit
breaker labeled ``FWD EVAP FAN,'' do the actions specified in
paragraphs (k)(1)(i) and (k)(1)(ii) of this AD, and document
deactivation of the system in the airplane logbook, referring to
this AD as the reason for deactivation. While the system is
deactivated, the airplane operator must remain aware of operating
temperature limitations specified in the applicable airplane flight
manual.
(3) For Model 560XL airplanes: Do the actions specified in
paragraphs (k)(1)(i) and (k)(1)(ii) of this AD, and document
deactivation of the system in the airplane logbook, referring to
this AD as the reason for
[[Page 32352]]
deactivation. While the system is deactivated, the airplane operator
must remain aware of operating temperature limitations specified in
the applicable airplane flight manual. Remove the fuse limiter that
supplies power to the A/C compressor motor by doing the actions
specified in paragraphs (k)(3)(i) through (k)(3)(viii) of this AD,
and return to the airplane to service by doing the actions specified
in paragraphs (k)(3)(ix) through (k)(3)(xiii) of this AD.
(i) Open the battery door.
(ii) Disconnect the main battery connector and remove external
electrical power.
(iii) Tag the battery and external power receptacle with a
warning tag that reads: ``WARNING: Do not connect the battery
connector during the maintenance in progress.''
(iv) Gain access to the J-Box through the tailcone access door.
(v) Remove the wing nuts that attach the cover to the J-Box.
(vi) Remove the J-Box cover.
(vii) Remove nuts securing compressor fuse limiter (reference
designator HZ116, P/N ANL130) to the bus bar.
(viii) Remove the compressor motor fuse limiter from the
terminals and retain for future reinstallation once the compressor
motor brushes have been replaced.
(ix) Install fuse limiter nuts on the terminals and torque to
100 inch-pounds +/- 5 inch-pounds.
(x) Install the J-Box cover with wing nuts.
(xi) Remove the warning tag on the battery and external power
receptacle.
(xii) Connect the battery and restore electrical power to the
airplane.
(xiii) Close the tailcone access door.
(l) Reactivation of A/C System
If an operator chooses to deactivate the A/C system, as
specified in paragraph (k) of this AD, and then later chooses to
return the A/C system to service: Before returning the A/C system to
service and removing the placard, perform the inspection specified
in paragraph (h) of this AD, and do the replacements specified in
paragraph (i) of this AD, at the times specified in paragraph (i) of
this AD. Return the A/C system to service by doing the actions
specified in paragraph (l)(1), (l)(2), or (l)(3) of this AD, as
applicable.
(1) For all airplanes except Model 560XL and 650 airplanes: Push
in the vapor cycle A/C circuit breaker labeled ``AIR COND,'' remove
the placard by the A/C selection switch that states ``A/C
DISABLED,'' and document reactivation of the system in the airplane
logbook.
(2) For Model 650 airplanes: Push in the vapor cycle A/C circuit
breaker labeled ``FWD EVAP FAN,'' remove the placard by the A/C
selection switch that states ``A/C DISABLED,'' and document
reactivation of the system in the airplane logbook.
(3) For Model 560XL airplanes: Remove the placard by the A/C
selection switch that states ``A/C DISABLED,'' and document
reactivation of the system in the airplane logbook. Re-install the
fuse limiter by doing the actions specified in paragraphs (l)(3)(i)
through (l)(3)(viii) of this AD, and return to the airplane to
service by doing the actions specified in paragraphs (l)(3)(ix)
through (l)(3)(xiii) of this AD.
(i) Open the battery door.
(ii) Disconnect the main battery connector and remove external
electrical power.
(iii) Tag the battery and external power receptacle with a
warning tag that reads: ``WARNING: Do not connect the battery
connector during the maintenance in progress.''
(iv) Gain access to the J-Box through the tailcone access door.
(v) Remove the wing nuts that attach the cover to the J-Box.
(vi) Remove the J-Box cover.
(vii) Remove the fuse limiter nuts on the bus bar terminals for
the fuse limiter.
(viii) Install the compressor motor fuse limiter (reference
designator HZ116, P/N ANL130).
(ix) Install fuse limiter nuts on the terminals and torque to
100 inch-pounds +/- 5 inch-pounds.
(x) Install the J-Box cover with wing nuts.
(xi) Remove the warning tag on the battery and external power
receptacle.
(xii) Connect the battery and restore electrical power to the
airplane.
(xiii) Close the tailcone access door.
(m) Parts Return and Reporting Requirements
For the first two A/C compressor motor brush replacement cycles
on each airplane, send the brushes that were removed to Cessna
Aircraft Company, Cessna Service Parts and Programs, 7121 Southwest
Boulevard, Wichita, KS 67215. Provide the brushes and the
information specified in paragraphs (m)(1) through (m)(6) of this AD
within 30 days after the replacement, if the replacement was done on
or after the effective date of this AD, or within 30 days after the
effective date of this AD, if the replacement was done before the
effective date of this AD.
(1) The model and serial number of the airplane.
(2) The part number of the motor.
(3) The part number of the brushes, if known.
(4) The elapsed amount of motor hours since the last brush/motor
replacement, if known.
(5) If motor hours are unknown, report the elapsed airplane
flight hours since the last brush/motor replacement and indicate
that motor hours are unknown.
(6) The number of motor hours currently displayed on the pallet
hour meter.
(n) Parts Installation Limitation
As of the effective date of this AD, no person may install an A/
C compressor motor having P/N 1134104-1 or P/N 1134104-5, unless the
inspection specified in paragraph (h) of this AD is done before
further flight, and the replacements specified in paragraph (i) of
this AD are done at the times specified in paragraph (i) of this AD.
(o) Special Flight Permit Limitation
Operation of the A/C system is prohibited while flying with a
special flight permit issued for this AD.
(p) Paperwork Reduction Act Burden Statement
A federal agency may not conduct or sponsor, and a person is not
required to respond to, nor shall a person be subject to a penalty
for failure to comply with a collection of information subject to
the requirements of the Paperwork Reduction Act unless that
collection of information displays a current valid OMB Control
Number. The OMB Control Number for this information collection is
2120-0056. Public reporting for this collection of information is
estimated to be approximately 5 minutes per response, including the
time for reviewing instructions, completing and reviewing the
collection of information. All responses to this collection of
information are mandatory. Comments concerning the accuracy of this
burden and suggestions for reducing the burden should be directed to
the FAA at: 800 Independence Ave. SW., Washington, DC 20591, Attn:
Information Collection Clearance Officer, AES-200.
(q) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Wichita 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 the Related Information
section 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.
(r) Related Information
For more information about this AD, contact Christine Abraham,
Aerospace Engineer, Electrical Systems and Avionics Branch, ACE-
119W, FAA, Wichita Aircraft Certification Office (ACO), 1801 Airport
Road, Room 100, Mid-Continent Airport, Wichita, Kansas 67209; phone:
316-946-4165; fax: 316-946-4107; email: wichita-cos@faa.gov.
(s) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do
the actions required by this AD, unless the AD specifies otherwise.
(i) Subject 4-11-00, Replacement Time Limits, of Chapter 4,
Airworthiness Limitations, Revision 10, dated April 23, 2012, of the
Cessna Model 550 Bravo Maintenance Manual. The revision level of
Chapter 4 is identified only on the title page of Chapter 4.
(ii) Subject 4-11-00, Replacement Time Limits, of Chapter 4,
Airworthiness Limitations, Revision 8, dated April 23, 2012, of the
Cessna Model 550 Maintenance Manual. The revision level of Chapter 4
is
[[Page 32353]]
identified only on the title page of Chapter 4.
(iii) Subject 4-11-00, Replacement Time Limits, of Chapter 4,
Airworthiness Limitations, Revision 20, dated April 23, 2012, of the
Cessna Model 560 Maintenance Manual. The revision level of Chapter 4
is identified only on the title page of Chapter 4.
(iv) Subject 4-11-00, Replacement Time Limits, of Chapter 4,
Airworthiness Limitations, Revision 13, dated April 23, 2012, of the
Cessna Model 560XL Maintenance Manual. The revision level of Chapter
4 is identified only on the title page of Chapter 4.
(v) Subject 4-11-00, Replacement Time Limits, of Chapter 4,
Airworthiness Limitations, Revision 30, dated April 23, 2012, of the
Cessna Model 650 Maintenance Manual. The revision level of Chapter 4
is identified only on the title page of Chapter 4.
(vi) Subject 4-11-00, Replacement Time Limits-General, of
Chapter 4, Airworthiness Limitations, Revision 4, dated April 23,
2012, of the Cessna Model 500/501Maintenance Manual. The revision
level of Chapter 4 is identified only on the title page of Chapter
4.
(vii) Subject 4-11-00, Replacement Time Limits, of Chapter 4,
Airworthiness Limitations, Revision 7, dated April 23, 2012, of the
Cessna Model S550 Maintenance Manual. The revision level of Chapter
4 is identified only on the title page of Chapter 4.
(3) For Cessna service information identified in this AD,
contact Cessna Aircraft Co., P.O. Box 7706, Wichita, KS 67277;
telephone 316-517-6215; fax 316-517-5802; email
citationpubs@cessna.textron.com; Internet https://www.cessnasupport.com/newlogin.html.
(4) You may view this service information at 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.
(5) You may view this service information that is incorporated
by reference 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 April 26, 2013.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2013-12662 Filed 5-29-13; 8:45 am]
BILLING CODE 4910-13-P
