Airworthiness Directives; Cessna Aircraft Company Airplanes, 55770-55773 [2012-22332]
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Federal Register / Vol. 77, No. 176 / Tuesday, September 11, 2012 / Proposed Rules
Perform and meet the low pressure leak test,
in accordance with the Accomplishment
Instructions of Boeing Special Attention
Service Bulletin 777–35–0024, dated
September 1, 2011.
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):
The Boeing Company: Docket No. FAA–
2012–0932; Directorate Identifier 2012–
NM–014–AD.
(a) Comments Due Date
We must receive comments by October 26,
2012.
(b) Affected ADs
None.
(c) Applicability
This AD applies to The Boeing Company
Model 777–200, –200LR, –300, –300ER, and
777F series airplanes; certificated in any
category; as identified in Boeing Special
Attention Service Bulletin 777–35–0024,
dated September 1, 2011.
(d) Subject
Joint Aircraft System Component (JASC)/
Air Transport Association (ATA) of America
Code 35, Oxygen.
Issued in Renton, Washington, on
September 4, 2012.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
(h) Corrective Action if Clamshell Coupler Is
Not Fully Latched
[FR Doc. 2012–22341 Filed 9–10–12; 8:45 am]
If, during any inspection required by
paragraph (g) of this AD, any clamshell
coupler is not fully latched: Before further
flight, latch the clamshell coupler, in
accordance with the Accomplishment
Instructions of Boeing Special Attention
Service Bulletin 777–35–0024, dated
September 1, 2011.
(i) Corrective Action if Clamshell Coupler Is
Not Installed
If, during any inspection required by
paragraph (g) of this AD, any clamshell
coupler is not installed: Before further flight,
install a clamshell coupler.
Note 1 to paragraph (i) of this AD:
Guidance on installation of the clamshell
coupler may be found in Subject 35–00–00,
Oxygen, of Chapter 35, Oxygen, of Part II,
Practices and Procedures, of the Boeing 777
Aircraft Maintenance Manual, Revision 65,
May 5, 2012.
(j) Alternative Methods of Compliance
(AMOCs)
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
srobinson on DSK4SPTVN1PROD with PROPOSALS
(e) Unsafe Condition
This AD was prompted by a report that
during a test of the oxygen system, an
operator found that the passenger oxygen
masks did not properly flow oxygen and that
a loud noise occurred in the overhead area,
which was caused by the flex line separating
from the hard line due to a missing clamshell
coupler. We are issuing this AD to prevent
the oxygen system flex line from separating
from the hard line, which could cause an
oxygen leak and a drop in the oxygen system
pressure, resulting in improper flow of
oxygen through the passenger masks and
injury to passengers if emergency oxygen is
needed.
(1) The Manager, Seattle 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.
Information may be emailed to: 9-ANMSeattle-ACO-AMOC-Requests@faa.gov.
(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.
(k) Related Information
(g) Inspection
Within 36 months after the effective date
of this AD, do the applicable actions in
paragraph (g)(1) or (g)(2) of this AD.
(1) For Groups 1–6, 8 and 9 airplanes, as
identified in Boeing Special Attention
Service Bulletin 777–35–0024, dated
September 1, 2011: Do a detailed inspection
of certain areas of the airplane oxygen system
to ensure clamshell couplers are installed
and fully latched, and perform and meet the
requirements of the low pressure leak test, in
accordance with the Accomplishment
Instructions of Boeing Special Attention
Service Bulletin 777–35–0024, dated
September 1, 2011.
(2) For Group 7 airplanes, as identified in
Boeing Special Attention Service Bulletin
777–35–0024, dated September 1, 2011:
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(1) For more information about this AD,
contact Susan Monroe, Aerospace Engineer,
Cabin Safety and Environmental Systems
Branch, ANM–150S, FAA, Seattle Aircraft
Certification Office, 1601 Lind Avenue SW.,
Renton, WA 98057–3356; phone: 425–917–
6457; fax: 425–917–6590; email:
susan.l.monroe@faa.gov.
(2) For service information identified in
this AD, contact Boeing Commercial
Airplanes, Attention: Data & Services
Management, P.O. Box 3707, MC 2H–65,
Seattle, Washington 98124–2207; telephone
206–544–5000, extension 1; fax 206–766–
5680; Internet https://
www.myboeingfleet.com. You may review
copies of the referenced service information
at the FAA, Transport Airplane Directorate,
1601 Lind Avenue SW., Renton, Washington.
For information on the availability of this
material at the FAA, call 425–227–1221.
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BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2012–0962; Directorate
Identifier 2012–CE–033–AD]
RIN 2120–AA64
Airworthiness Directives; Cessna
Aircraft Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to adopt a new
airworthiness directive (AD) for certain
Cessna Aircraft Company Models
172RG, R182, TR182, FR182, 210N,
T210N, 210R, T210R, P210N, P210R,
and T303 airplanes. This proposed AD
was prompted by a report of a cockpit
fire that appeared to originate from the
area of the landing gear’s hydraulic
power pack system. This proposed AD
would require you inspect the aircraft’s
hydraulic power pack wiring for
incorrect installation, and if needed,
correct the installation. We are
proposing this AD to correct the unsafe
condition on these products.
DATES: We must receive comments on
this proposed AD by October 26, 2012.
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 Cessna
Aircraft Company, Customer Service,
P.O. Box 7706, Wichita, KS 67277;
telephone: (316) 517–5800; fax: (316)
517–7271; Internet: https://
www.cessna.com/customer-service/
SUMMARY:
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Federal Register / Vol. 77, No. 176 / Tuesday, September 11, 2012 / Proposed Rules
technical-publications.html. You may
review copies of the referenced service
information at the FAA, Small Airplane
Directorate, 901 Locust, Kansas City,
MO 64106. For information on the
availability of this material at the FAA,
call (816) 329–4148.
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:
Richard Rejniak, Aerospace Engineer,
Wichita Aircraft Certification Office,
1801 Airport Road, Room 100, Wichita,
Kansas 67209; phone: (316) 946–4128;
fax: (316) 946–4107; email:
richard.rejniak@faa.gov.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposal. Send your comments to
an address listed under the ADDRESSES
section. Include ‘‘Docket No. FAA–
2012–0962; Directorate Identifier 2012–
CE–033–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
We received a report of an accident of
a Cessna Aircraft Company Model
172RG airplane where a fire started inflight on the cabin side of the firewall
and rapidly accelerated. The fire
originated from the area of the landing
gear’s hydraulic power pack system and
resulted in a complete hull loss with
reported injuries.
The investigation concluded that an
in-flight fire may result from improper
installation of the terminal lugs,
improper installation of (or missing)
terminal covers and associated wiring to
the landing gear hydraulic power pack
motor wiring, which was not properly
protected or adequately secured. The
cause for the rapid acceleration of the
fire was indicative of the presence of
flammable materials or a flammable
material source near or in contact with
the hydraulic power pack system within
the aircraft’s cockpit/cabin.
This style of hydraulic power pack is
also used on Cessna Aircraft Company
Models R182, TR182, FR182, 210N,
T210N, 210R, T210R, P210N, P210R,
and T303 airplanes.
This condition, if not corrected, could
result in a fire in the aircraft’s cockpit,
damage and or loss of aircraft, and
injuries and or fatalities.
Relevant Service Information
We reviewed Cessna Aircraft
Company Service Letter MEL–29–01,
dated July 14, 2012; and Service Letter
SEL–29–01, dated July 16, 2012. The
service information describes
procedures for inspection of the
aircraft’s hydraulic power pack system
for proper wire routing, protective
cover, and hydraulic leaks, and if
needed, installation of a protective
cover and rerouting of wiring.
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 these same
type designs.
Proposed AD Requirements
This proposed AD would require
accomplishing the actions specified in
the service information described
previously.
Costs of Compliance
We estimate that this proposed AD
affects 2,961 airplanes of U.S. registry.
We estimate the following costs to
comply with this proposed AD:
ESTIMATED COSTS
Action
Labor cost
Parts cost
Cost per
product
Cost on U.S.
operators
Hydraulic power pack system wiring inspection.
1 work-hour × $85 per hour = $85 ...........
Not applicable ...........
$85
$251,685
We estimate the following costs to do
any necessary hydraulic power pack
terminal lug protective cap installation
that would be required based on the
results of the proposed inspection. We
have no way of determining the number
of aircraft that might need this
installation:
ON-CONDITION COSTS
Labor cost
Parts cost
Cost per
product
Hydraulic power pack system wiring installation ..........
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Action
1 work-hour × $85 per hour = $85 ...............................
$29
$114
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:
VerDate Mar<15>2010
18:01 Sep 10, 2012
Jkt 226001
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:
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‘‘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
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Federal Register / Vol. 77, No. 176 / Tuesday, September 11, 2012 / Proposed Rules
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
Regulatory Findings
We determined that this proposed AD
would not have federalism implications
under Executive Order 13132. This
proposed AD would not have a
substantial direct effect on the States, on
the relationship between the national
Government and the States, or on the
distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify this proposed regulation:
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866,
(2) Is not a ‘‘significant rule’’ under
the DOT Regulatory Policies and
Procedures (44 FR 11034, February 26,
1979),
(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.
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
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):
Cessna Aircraft Company: Docket No. FAA–
2012–0962+; Directorate Identifier 2012–
CE–033–AD.
(a) Comments Due Date
We must receive comments by October 26,
2012.
(b) Affected ADs
None.
(c) Applicability
This AD applies to the following Cessna
Aircraft Company airplanes, certificated in
any category, as identified in table 1,
paragraph (c), of this AD:
1. The authority citation for part 39
continues to read as follows:
TABLE 1 TO PARAGRAPH (c) OF THIS AD—APPLICABILITY
Model
(1)
(2)
(3)
(4)
(5)
(6)
(7)
172RG .........................................................................................................................................................
R182 and TR182 .........................................................................................................................................
FR182 ..........................................................................................................................................................
210N, T210N, 210R, and T210R ................................................................................................................
P210N ..........................................................................................................................................................
P210R ..........................................................................................................................................................
T303 .............................................................................................................................................................
(d) Subject
Joint Aircraft System Component (JASC)/
Air Transport Association (ATA) of America
Code 32, Landing Gear.
(e) Unsafe Condition
This AD was prompted by a report of a
cockpit fire that appeared to originate from
the area of the landing gear’s hydraulic
power pack system. We are issuing this AD
to correct the unsafe condition on these
products.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
srobinson on DSK4SPTVN1PROD with PROPOSALS
Serial Nos.
(g) Inspect the Hydraulic Power Pack Wiring
for Correct Installation
(1) Single engine aircraft: Within the next
100 hours time-in-service (TIS) after the
effective date of this AD or within the next
12 calendar months after the effective date of
this AD, whichever occurs first, inspect the
hydraulic power pack wiring for correct
installation. Follow Cessna Aircraft Company
Service Letter SEL–29–01, dated July 16,
2012.
(2) Multi-engine aircraft: Within the next
100 hours TIS after the effective date of this
AD or within the next 12 calendar months
after the effective date of this AD, whichever
occurs first, inspect the hydraulic power
VerDate Mar<15>2010
18:01 Sep 10, 2012
Jkt 226001
pack wiring for correct installation. Follow
Cessna Aircraft Company Service Letter
MEL–29–01, dated July 14, 2012.
(h) Correct the Installation of the Hydraulic
Power Pack Wiring
(1) Single engine aircraft: If you find
evidence of incorrect installation of the
hydraulic power pack wiring as a result of
the inspection required by paragraph (g)(1) of
this AD, before further flight, correct the
installation. Follow Cessna Aircraft Company
Service Letter SEL–29–01, dated July 16,
2012.
(2) Multi-engine aircraft: If you find
evidence of incorrect installation of the
hydraulic power pack wiring as a result of
the inspection required by paragraph (g)(2) of
this AD, before further flight, correct the
installation. Follow Cessna Aircraft Company
Service Letter MEL–29–01, dated July 14,
2012.
(i) Special Flight Permit
Special flight permits are permitted with
the following limitation: visual flight rules
(VFR) day conditions.
(j) 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
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172RG000l through 172RG1191.
R18200584 through Rl8202039.
FR18200021 through FR18200070.
21062955 through 21065009.
P21000151 through P21000834.
P21000835 through P21000874.
T30300001 through T30300315.
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.
(k) Related Information
(1) For more information about this AD,
contact Richard Rejniak, Aerospace Engineer,
Wichita ACO, 1801 Airport Road, Room 100,
Wichita, Kansas 67209; phone: (316) 946–
4128; fax: (316) 946–4107; email:
richard.rejniak@faa.gov.
(2) For service information identified in
this AD, contact Cessna Aircraft Company,
Customer service, P.O. Box 7706, Wichita, KS
67277; telephone: (316) 517–5800; fax: (316)
517–7271; Internet: https://
www.cessnasupport.com/customer-service/
technical-publications.html. You may review
copies of the referenced service information
at the FAA, Small Airplane Directorate, 901
Locust, Kansas City, MO 64106. For
information on the availability of this
material at the FAA, call (816) 329–4148.
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Federal Register / Vol. 77, No. 176 / Tuesday, September 11, 2012 / Proposed Rules
Issued in Kansas City, Missouri, on
September 5, 2012.
Earl Lawrence,
Manager, Small Airplane Directorate, Aircraft
Certification Service.
[FR Doc. 2012–22332 Filed 9–10–12; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2011–0909; Directorate
Identifier 2011–NM–027–AD]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Supplemental notice of
proposed rulemaking (NPRM);
reopening of comment period.
AGENCY:
We are revising an earlier
proposed airworthiness directive (AD)
for all The Boeing Company Model DC–
9–81 (MD–81), DC–9–82 (MD–82), DC–
9–83 (MD–83), DC–9–87 (MD–87), and
MD–88 airplanes. That NPRM proposed
repetitive high frequency eddy current
(HFEC) inspections for cracking of the
left and right rib hinge bearing lugs of
the aft face of the center section of the
horizontal stabilizer; measuring crack
length and blending out cracks; and
replacing the horizontal stabilizer center
section rib, if necessary. That NPRM
was prompted by reports of cracks of the
hinge bearing lugs of the center section
ribs of the horizontal stabilizer. This
action revises that NPRM by adding the
requirement for rib replacement if
cracking is found during certain
inspections of this proposed AD. We are
proposing this supplemental NPRM to
detect and correct cracking in the hinge
bearing lugs of the horizontal stabilizer
center section ribs, which could result
in failure of the lugs, resulting in the
inability of the horizontal stabilizer to
sustain the required limit loads and
consequent loss of control of the
airplane. Since these actions impose an
additional burden over that proposed in
the NPRM, we are reopening the
comment period to allow the public the
chance to comment on these proposed
changes.
DATES: We must receive comments on
this supplemental NPRM by October 26,
2012.
ADDRESSES: You may send comments,
using the procedures found in 14 CFR
11.43 and 11.45, by any of the following
methods:
srobinson on DSK4SPTVN1PROD with PROPOSALS
SUMMARY:
VerDate Mar<15>2010
18:01 Sep 10, 2012
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• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: 202–493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE.,
Washington, DC 20590.
• Hand Delivery: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE.,
Washington, DC 20590, between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays.
For service information identified in
this proposed AD, contact Boeing
Commercial Airplanes, Attention: Data
& Services Management, 3855
Lakewood Boulevard, MC D800–0019,
Long Beach, CA 90846–0001; telephone
206–544–5000, extension 2; fax 206–
766–5683; Internet https://
www.myboeingfleet.com. You may
review copies of the referenced service
information at the FAA, Transport
Airplane Directorate, 1601 Lind Avenue
SW., Renton, Washington. For
information on the availability of this
material at the FAA, call 425–227–1221.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov; or in person at the
Docket Management Facility between 9
a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The AD
docket contains this proposed AD, the
regulatory evaluation, any comments
received, and other information. The
street address for the Docket Office
(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, Aerospace Engineer,
Airframe Branch, ANM–120L, FAA, Los
Angeles Aircraft Certification Office,
3960 Paramount Boulevard, Lakewood,
CA 90712–4137; phone: (562) 627–5233;
fax: (562) 627–5210; email:
roger.durbin@faa.gov.
SUPPLEMENTARY INFORMATION:
55773
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
We issued an NPRM to amend 14 CFR
part 39 to include an AD that would
apply to The Boeing Company Model
DC–9–81 (MD–81), DC–9–82 (MD–82),
DC–9–83 (MD–83), DC–9–87 (MD–87),
and MD–88 airplanes. That NPRM
published in the Federal Register on
August 26, 2011 (76 FR 53346). That
NPRM proposed to require repetitive
HFEC inspections for cracking of the left
and right rib hinge bearing lugs of the
aft face of the center section of the
horizontal stabilizer; measuring crack
length and blending out cracks; and
replacing the horizontal stabilizer center
section rib, if necessary.
Actions Since NPRM (76 FR 53346,
August 26, 2011) Was Issued
Since we issued the previous NPRM
(76 FR 53346, August 26, 2011), we
determined a required corrective action
was not specified by Boeing Alert
Service Bulletin MD80–55A069, dated
January 19, 2011. Therefore, we propose
to add a requirement for rib replacement
if cracking is found during certain
inspections required by this
supplemental NPRM.
Comments
We gave the public the opportunity to
comment on the previous NPRM (76 FR
53346, August 26, 2011). The following
presents the comments received on the
NPRM and the FAA’s response to each
comment.
Support for the NPRM (76 FR 53346,
August 26, 2011)
Boeing stated it supports the NPRM
(76 FR 53346, August 26, 2011).
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–2011–0909; Directorate Identifier
2011–NM–027–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
Recognition That Reporting of Findings
Is Not Required
American Airlines stated it recognizes
that reporting of findings requested by
Boeing Alert Service Bulletin MD80–
55A069, dated January 19, 2011, is not
required by the NPRM (76 FR 53346,
August 26, 2011).
We acknowledge American Airlines’s
comment. Reporting is not required by
the supplemental NPRM. We have not
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]]>Agencies
[Federal Register Volume 77, Number 176 (Tuesday, September 11, 2012)]
[Proposed Rules]
[Pages 55770-55773]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2012-22332]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2012-0962; Directorate Identifier 2012-CE-033-AD]
RIN 2120-AA64
Airworthiness Directives; Cessna Aircraft Company Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to adopt a new airworthiness directive (AD) for
certain Cessna Aircraft Company Models 172RG, R182, TR182, FR182, 210N,
T210N, 210R, T210R, P210N, P210R, and T303 airplanes. This proposed AD
was prompted by a report of a cockpit fire that appeared to originate
from the area of the landing gear's hydraulic power pack system. This
proposed AD would require you inspect the aircraft's hydraulic power
pack wiring for incorrect installation, and if needed, correct the
installation. We are proposing this AD to correct the unsafe condition
on these products.
DATES: We must receive comments on this proposed AD by October 26,
2012.
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
Cessna Aircraft Company, Customer Service, P.O. Box 7706, Wichita, KS
67277; telephone: (316) 517-5800; fax: (316) 517-7271; Internet: http:/
/www.cessna.com/customer-service/
[[Page 55771]]
technical-publications.html. You may review copies of the referenced
service information at the FAA, Small Airplane Directorate, 901 Locust,
Kansas City, MO 64106. For information on the availability of this
material at the FAA, call (816) 329-4148.
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: Richard Rejniak, Aerospace Engineer,
Wichita Aircraft Certification Office, 1801 Airport Road, Room 100,
Wichita, Kansas 67209; phone: (316) 946-4128; fax: (316) 946-4107;
email: richard.rejniak@faa.gov.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposal. Send your comments to an address listed
under the ADDRESSES section. Include ``Docket No. FAA-2012-0962;
Directorate Identifier 2012-CE-033-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
We received a report of an accident of a Cessna Aircraft Company
Model 172RG airplane where a fire started in-flight on the cabin side
of the firewall and rapidly accelerated. The fire originated from the
area of the landing gear's hydraulic power pack system and resulted in
a complete hull loss with reported injuries.
The investigation concluded that an in-flight fire may result from
improper installation of the terminal lugs, improper installation of
(or missing) terminal covers and associated wiring to the landing gear
hydraulic power pack motor wiring, which was not properly protected or
adequately secured. The cause for the rapid acceleration of the fire
was indicative of the presence of flammable materials or a flammable
material source near or in contact with the hydraulic power pack system
within the aircraft's cockpit/cabin.
This style of hydraulic power pack is also used on Cessna Aircraft
Company Models R182, TR182, FR182, 210N, T210N, 210R, T210R, P210N,
P210R, and T303 airplanes.
This condition, if not corrected, could result in a fire in the
aircraft's cockpit, damage and or loss of aircraft, and injuries and or
fatalities.
Relevant Service Information
We reviewed Cessna Aircraft Company Service Letter MEL-29-01, dated
July 14, 2012; and Service Letter SEL-29-01, dated July 16, 2012. The
service information describes procedures for inspection of the
aircraft's hydraulic power pack system for proper wire routing,
protective cover, and hydraulic leaks, and if needed, installation of a
protective cover and rerouting of wiring.
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 these same type
designs.
Proposed AD Requirements
This proposed AD would require accomplishing the actions specified
in the service information described previously.
Costs of Compliance
We estimate that this proposed AD affects 2,961 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
----------------------------------------------------------------------------------------------------------------
Hydraulic power pack system 1 work-hour x $85 Not applicable............. $85 $251,685
wiring inspection. per hour = $85.
----------------------------------------------------------------------------------------------------------------
We estimate the following costs to do any necessary hydraulic
power pack terminal lug protective cap installation that would be
required based on the results of the proposed inspection. We have no
way of determining the number of aircraft that might need this
installation:
On-Condition Costs
----------------------------------------------------------------------------------------------------------------
Cost per
Action Labor cost Parts cost product
----------------------------------------------------------------------------------------------------------------
Hydraulic power pack system wiring 1 work-hour x $85 per hour = $29 $114
installation. $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
[[Page 55772]]
safety in air commerce. This regulation is within the scope of that
authority because it addresses an unsafe condition that is likely to
exist or develop on products identified in this rulemaking action.
Regulatory Findings
We determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect on the States, on the relationship
between the national Government and the States, or on the distribution
of power and responsibilities among the various levels of government.
For the reasons discussed above, I certify this proposed
regulation:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979),
(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.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
2. The FAA amends Sec. 39.13 by adding the following new
airworthiness directive (AD):
Cessna Aircraft Company: Docket No. FAA-2012-0962+; Directorate
Identifier 2012-CE-033-AD.
(a) Comments Due Date
We must receive comments by October 26, 2012.
(b) Affected ADs
None.
(c) Applicability
This AD applies to the following Cessna Aircraft Company
airplanes, certificated in any category, as identified in table 1,
paragraph (c), of this AD:
Table 1 to Paragraph (c) of This AD--Applicability
----------------------------------------------------------------------------------------------------------------
Model Serial Nos.
----------------------------------------------------------------------------------------------------------------
(1) 172RG....................................... 172RG000l through 172RG1191.
(2) R182 and TR182.............................. R18200584 through Rl8202039.
(3) FR182....................................... FR18200021 through FR18200070.
(4) 210N, T210N, 210R, and T210R................ 21062955 through 21065009.
(5) P210N....................................... P21000151 through P21000834.
(6) P210R....................................... P21000835 through P21000874.
(7) T303........................................ T30300001 through T30300315.
----------------------------------------------------------------------------------------------------------------
(d) Subject
Joint Aircraft System Component (JASC)/Air Transport Association
(ATA) of America Code 32, Landing Gear.
(e) Unsafe Condition
This AD was prompted by a report of a cockpit fire that appeared
to originate from the area of the landing gear's hydraulic power
pack system. We are issuing this AD to correct the unsafe condition
on these products.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Inspect the Hydraulic Power Pack Wiring for Correct Installation
(1) Single engine aircraft: Within the next 100 hours time-in-
service (TIS) after the effective date of this AD or within the next
12 calendar months after the effective date of this AD, whichever
occurs first, inspect the hydraulic power pack wiring for correct
installation. Follow Cessna Aircraft Company Service Letter SEL-29-
01, dated July 16, 2012.
(2) Multi-engine aircraft: Within the next 100 hours TIS after
the effective date of this AD or within the next 12 calendar months
after the effective date of this AD, whichever occurs first, inspect
the hydraulic power pack wiring for correct installation. Follow
Cessna Aircraft Company Service Letter MEL-29-01, dated July 14,
2012.
(h) Correct the Installation of the Hydraulic Power Pack Wiring
(1) Single engine aircraft: If you find evidence of incorrect
installation of the hydraulic power pack wiring as a result of the
inspection required by paragraph (g)(1) of this AD, before further
flight, correct the installation. Follow Cessna Aircraft Company
Service Letter SEL-29-01, dated July 16, 2012.
(2) Multi-engine aircraft: If you find evidence of incorrect
installation of the hydraulic power pack wiring as a result of the
inspection required by paragraph (g)(2) of this AD, before further
flight, correct the installation. Follow Cessna Aircraft Company
Service Letter MEL-29-01, dated July 14, 2012.
(i) Special Flight Permit
Special flight permits are permitted with the following
limitation: visual flight rules (VFR) day conditions.
(j) 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.
(k) Related Information
(1) For more information about this AD, contact Richard Rejniak,
Aerospace Engineer, Wichita ACO, 1801 Airport Road, Room 100,
Wichita, Kansas 67209; phone: (316) 946-4128; fax: (316) 946-4107;
email: richard.rejniak@faa.gov.
(2) For service information identified in this AD, contact
Cessna Aircraft Company, Customer service, P.O. Box 7706, Wichita,
KS 67277; telephone: (316) 517-5800; fax: (316) 517-7271; Internet:
https://www.cessnasupport.com/customer-service/technical-publications.html. You may review copies of the referenced service
information at the FAA, Small Airplane Directorate, 901 Locust,
Kansas City, MO 64106. For information on the availability of this
material at the FAA, call (816) 329-4148.
[[Page 55773]]
Issued in Kansas City, Missouri, on September 5, 2012.
Earl Lawrence,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2012-22332 Filed 9-10-12; 8:45 am]
BILLING CODE 4910-13-P
