[Federal Register Volume 75, Number 162 (Monday, August 23, 2010)]
[Proposed Rules]
[Pages 51701-51705]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2010-20853]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2010-0802; Directorate Identifier 2009-NM-256-AD]
RIN 2120-AA64
Airworthiness Directives; Learjet Inc. Model 45 Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: The FAA proposes to supersede an existing airworthiness
directive (AD) that applies to certain Learjet Inc. Model 45 airplanes.
The existing AD currently requires, for certain airplanes, repetitive
inspections for chafing and other damage of the case drain tube from
the hydraulic pump case installed on the left-hand engine, and
corrective action if necessary. The existing AD also requires, for all
airplanes, repetitive inspections for discrepancies of the left
engine's nacelle tubing, repetitive inspections for evidence of fluid
leakage within the left engine accessory compartment, and corrective
actions if necessary. This proposed AD would require replacing the left
engine fuel and hydraulic tubing and installing a tubing support
channel, which would terminate the repetitive inspections required in
the existing AD. This proposed AD also removes airplanes from the
applicability. This proposed AD results from reports of chafed
hydraulic tubes in the left-hand engine. We are proposing this AD to
detect and correct chafed hydraulic tubes in the left-hand engine and
consequent hydraulic tube failure and uncontrolled loss of flammable
fluid within the engine cowling, which could result in a fire in the
engine nacelle and loss of control of the airplane.
DATES: We must receive comments on this proposed AD by October 7, 2010.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Portal: Go to http://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
Learjet, Inc., One Learjet Way, Wichita, Kansas 67209-2942; telephone:
316-946-2000; fax: 316-946-2220; e-mail: [email protected];
Internet: http://www.bombardier.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 http://www.regulations.gov; or in person at the Docket Management Facility
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains this proposed AD, the regulatory
evaluation, any comments received, and other information. The street
address for the Docket Office (telephone 800-647-5527) is in the
ADDRESSES section. Comments will be available in the AD docket shortly
after receipt.
FOR FURTHER INFORMATION CONTACT: James Galstad, Aerospace Engineer,
Systems and Propulsion Branch, ACE-116W, FAA, Wichita Aircraft
Certification Office, 1801 Airport Road, Room 100, Mid-Continent
Airport, Wichita, Kansas 67209; telephone (316) 946-4135; fax (316)
946-4107.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2010-0802;
Directorate Identifier 2009-NM-256-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 http://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.
[[Page 51702]]
Discussion
On May 20, 2009, we issued AD 2009-11-13, amendment 39-15923 (74 FR
26288, June 2, 2009), for certain Learjet Inc. Model 45 airplanes. That
AD requires, for certain airplanes, repetitive inspections for chafing
and other damage of the case drain tube from the hydraulic pump case
installed on the left-hand engine, and corrective action if necessary.
This AD also requires, for all airplanes, repetitive inspections for
discrepancies of the left engine's nacelle tubing, repetitive
inspections for evidence of fluid leakage within the left engine
accessory compartment, and corrective actions if necessary. That AD
resulted from reports of chafed hydraulic tubes in the left-hand
engine. We issued that AD to detect and correct chafed hydraulic tubes
in the left-hand engine and consequent hydraulic tube failure and
uncontrolled loss of flammable fluid within the engine cowling, which
could result in a fire in the engine nacelle and loss of control of the
airplane.
Actions Since Existing AD Was Issued
The preamble to AD 2009-11-13 specifies that we consider the
requirements ``interim action'' and that the manufacturer is developing
a modification to address the unsafe condition. That AD explains that
we might consider further rulemaking if a modification is developed,
approved, and available. The manufacturer now has developed such a
modification, and we have determined that further rulemaking is indeed
necessary; this proposed AD follows from that determination.
Changes to the Applicability
The applicability of AD 2009-11-13 includes airplanes having serial
numbers (S/N) 45-002 through 45-4000 inclusive. This proposed AD would
apply to airplanes having S/Ns 45-005 through 45-405 inclusive, and 45-
2001 through 45-2126 inclusive. Airplanes having S/Ns 45-406 through
45-2000 and 45-2127 through 45-4000, have incorporated a design change
in production that addresses the identified unsafe condition, and
therefore we removed these airplanes from the applicability. We also
removed S/N 45-002 because it is an experimental airplane at Learjet,
and we removed S/Ns 45-003 and 45-004 because they no longer exist.
Relevant Service Information
We have reviewed Bombardier Service Bulletins 40-71-04 (Model 45,
serial numbers 45-2001 through 45-2126) and 45-71-7 (Model 45, serial
numbers 45-005 through 45-405), both dated December 7, 2009. These
service bulletins describe procedures for replacing the left engine
fuel and hydraulic tubing and installing a tubing support channel,
including doing a general visual inspection for galling of the fuel
supply manifold assembly, a general visual inspection for minimum
clearance between the firewall fuel supply tube assembly and the engine
firewall cutout, a general visual inspection for minimum clearance
between the lower nacelle hydraulic tube and hose assemblies, a general
visual inspection for minimum clearance between the lower nacelle fuel
tubes and flexible hoses, and corrective actions if necessary. The
corrective actions include replacing the fuel supply manifold, trimming
the cutout to meet minimum clearance specifications, and adjusting
parts to meet minimum clearance specifications. Modification of the
applicable in-service airplanes eliminates the need for the existing
requirements of AD 2009-11-13.
Bombardier Service Bulletin 45-71-7, dated December 7, 2009,
specifies prior or concurrent accomplishment of Bombardier Service
Bulletin 45-71-5, dated February 13, 2007, for airplanes having serial
numbers 45-005 through 45-319, and 45-321. Bombardier Service Bulletin
40-71-04, dated December 7, 2009, specifies prior or concurrent
accomplishment of Bombardier Service Bulletin 40-71-02, dated February
13, 2007, for airplanes having serial numbers 45-2001 through 45-2069.
Bombardier Service Bulletins 45-71-5 and 40-71-02, both dated February
13, 2007, describe the following procedures:
For certain airplanes, changing the routing and clamping
configuration of the engine and alternator wire harnesses, and the
starter/generator wire bundles.
For certain airplanes, doing a detailed inspection for
chafing of specific hydraulic tubes located within the left engine
nacelle between the adjacent fuel tubes and to determine if there is
interference between the fuel tubing and hydraulic tubing, securing the
hydraulic tubes with additional clamps, inspecting adjacent fuel tubing
for interference with the hydraulic tubing, and corrective actions if
necessary. Corrective actions include replacing chafed hydraulic tubes
and replacing fuel tubes if interference is found.
For certain airplanes, replacing the left engine hydraulic
pump case drain tube.
For certain airplanes, inspecting for clearance between
the left engine hydraulic tubing with adjacent tubing, structure, and
other components; and replacing tubing if necessary.
For all airplanes, inspecting for clearance between the
wire harnesses and the hydraulic and fuel tubing on the left engines,
if necessary; and replacing tubing if necessary.
For certain airplanes, inspecting for clearance between
the wire harnesses and the hydraulic and fuel tubing on the right
engines, if necessary; and replacing tubing if necessary.
FAA's Determination and Requirements of the Proposed AD
We have evaluated all pertinent information and identified an
unsafe condition that is likely to develop on other airplanes of the
same type design. For this reason, we are proposing this AD, which
would supersede AD 2009-11-13 and would retain the requirements of the
existing AD until the modification is done. This proposed AD would also
require accomplishing the actions specified in Bombardier Service
Bulletins 40-71-04 and 45-71-7, both dated December 7, 2009; and
Bombardier Service Bulletins 40-71-02 and 45-71-5, both dated February
13, 2007.
Costs of Compliance
There are about 530 airplanes of the affected design in the
worldwide fleet. The following table provides the estimated costs for
U.S. operators to comply with this proposed AD.
[[Page 51703]]
Estimated Costs
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Number of
Average U.S.-
Action Work hours labor rate Parts Cost per airplane registered Fleet cost
per hour airplanes
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Inspection (required by AD 2009-11- 3 $85 $0...................... $255 per inspection.... 325 $82,875 per inspection.
13).
Modification (new proposed action)... 20 85 Up to $14,740........... Up to $16,440.......... 358 Up to $5,885,520.
Concurrent Action.................... 4 85 $189.................... $529................... 358 $189,382.
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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 the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We have determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect on the States, on the relationship
between the national Government and the States, or on the distribution
of power and responsibilities among the various levels of government.
For the reasons discussed above, I certify that the proposed
regulation:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979); and
3. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
We prepared a regulatory evaluation of the estimated costs to
comply with this proposed AD and placed it in the AD docket. See the
ADDRESSES section for a location to examine the regulatory evaluation.
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 removing amendment 39-15923 (74 FR
26288, June 2, 2009) and adding the following new AD:
Learjet Inc.: Docket No. FAA-2010-0802; Directorate Identifier 2009-
NM-256-AD.
Comments Due Date
(a) The FAA must receive comments on this AD action by October
7, 2010.
Affected ADs
(b) This AD supersedes AD 2009-11-13, Amendment 39-15923.
Applicability
(c) This AD applies to Learjet Inc. Model 45 airplanes;
certificated in any category; serial numbers 45-005 through 45-405
inclusive, and 45-2001 through 45-2126 inclusive.
Subject
(d) Air Transport Association (ATA) of America Code 71:
Powerplant.
Unsafe Condition
(e) This AD results from reports of chafed hydraulic tubes in
the left-hand engine. The Federal Aviation Administration is issuing
this AD to detect and correct chafed hydraulic tubes in the left-
hand engine and consequent hydraulic tube failure and uncontrolled
loss of flammable fluid within the engine cowling, which could
result in a fire in the engine nacelle and loss of control of the
airplane.
Compliance
(f) You are responsible for having the actions required by this
AD performed within the compliance times specified, unless the
actions have already been done.
Restatement of Requirements of AD 2009-11-13, With No Changes
Repetitive Inspections: Case Drain Tube
(g) For airplanes having serial numbers identified in Table 1 of
this AD: Within 50 flight hours after June 17, 2009 (the effective
date of AD 2009-11-13), do a detailed inspection for chafing and
other damage of the case drain tube from the hydraulic pump case
installed on the left-hand engine, in accordance with the applicable
service bulletin identified in Table 1 of this AD. If any damage is
found, before further flight, reposition or replace the tube, as
applicable, in accordance with the Accomplishment Instructions of
the applicable service bulletin identified in Table 1 of this AD.
Repeat the inspection thereafter at intervals not to exceed 150
flight hours until the modification required by paragraph (l) of
this AD is done.
Table 1--Service Bulletins for Inspections
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For-- Use--
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Serial numbers 45-005 through 45-313 Bombardier Alert Service
inclusive (commonly referred to as Bulletin A45-29-15, dated
``M45'' airplanes). December 26, 2006.
Serial numbers 45-2001 through 45-2063 Bombardier Alert Service
inclusive (commonly referred to as Bulletin A40-29-03, dated
``M40'' airplanes). December 26, 2006.
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[[Page 51704]]
Note 1: For the purposes of this AD, a detailed inspection is:
``An intensive examination of a specific item, installation, or
assembly to detect damage, failure, or irregularity. Available
lighting is normally supplemented with a direct source of good
lighting at an intensity deemed appropriate. Inspection aids such as
mirror, magnifying lenses, etc., may be necessary. Surface cleaning
and elaborate procedures may be required.''
Repetitive Inspections: Nacelle Tubing
(h) Within 50 flight hours after June 17, 2009, do a detailed
inspection for discrepancies of the left engine's nacelle tubing, in
accordance with the applicable temporary revision (TR) identified in
Table 2 of this AD. Discrepancies include damaged tubing, and
inadequate clearance between any unsupported section of the tube or
other tubing and surrounding components. If any discrepancy is
found, before further flight, adjust the tubing and clamping or
replace the tubing, as applicable, in accordance with the applicable
TR identified in Table 2 of this AD. Repeat the inspection
thereafter at intervals not to exceed 150 flight hours until the
modification required by paragraph (l) of this AD is done.
Table 2--TRs for Inspections
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For-- Use--
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Serial numbers 45-2001 through 45-4000 Learjet 40 TR 71-1, dated April
inclusive (commonly referred to as 28, 2009, to the Learjet 40
``M40'' airplanes). Maintenance Manual MM-105.
Serial numbers 45-002 through 45-2000 Learjet 45 TR 71-1, dated April
inclusive (commonly referred to as 28, 2009, to the Learjet 45
``M45'' airplanes). Maintenance Manual MM-104.
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Concurrent Inspections: Fluid Leakage
(i) Concurrently with each inspection required by paragraph (h)
of this AD, do a detailed inspection for evidence of engine oil,
hydraulic fluid, or fuel leakage within the left engine accessory
compartment, in accordance with the applicable maintenance manual
section identified in Table 3 of this AD. If there is evidence of
leakage: Before further flight, remove each plumbing clamp within
the inspection areas specified in paragraphs (g) and (h) of this AD,
and clean and remove all evidence of fluid leakage.
Table 3--Maintenance Manual Sections for Inspections
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For-- Use--
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Serial numbers 45-002 through 45-2000 Section 71-00-00, ``Powerplant--
inclusive (commonly referred to as Maintenance Practices,'' and
``M45'' airplanes). Section 71-00-01, ``Engine--
Maintenance Practices,'' of
the Learjet 45 Maintenance
Manual MM-104, Revision 47,
dated March 30, 2009.
Serial numbers 45-2001 through 45-4000 Section 71-00-01, ``Engine--
inclusive (commonly referred to as Maintenance Practices,'' of
``M40'' airplanes). the Learjet 40 Maintenance
Manual MM-105, Revision 15,
dated March 30, 2009.
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Additional Corrective Action for Fluid Leakage and Inadequate Clearance
(j) If evidence of fluid leakage was found during any inspection
required by paragraph (i) of this AD, or if inadequate clearance was
found during any action required by paragraph (g) or (h) of this AD:
Before further flight, replace each clamp associated with the fluid
leakage or inadequate clearance with a new clamp, in accordance with
the applicable maintenance manual identified in Table 3 of this AD.
Parts Installation
(k) As of June 17, 2009, no person may re-install, on any
airplane, any plumbing clamp that has been removed in accordance
with the requirements of paragraphs (g), (h), (i), or (j) of this
AD.
New Requirements of This AD
Terminating Action
(l) Within 300 flight hours or 12 months after the effective
date of this AD, whichever occurs first, do the actions specified in
paragraphs (l)(1) and (l)(2) of this AD, in accordance with the
Accomplishment Instructions of Bombardier Service Bulletin 40-71-04
(Model 45, serial numbers 45-2001 through 45-2126) or 45-71-7 (Model
45, serial numbers 45-005 through 45-405), both dated December 7,
2009, as applicable. Accomplishment of the requirements of
paragraphs (l) and (m), as applicable, of this AD terminates the
requirements of paragraphs (g), (h), (i), and (j) of this AD.
(1) Replace the left engine fuel and hydraulic tubing and
install a tubing support channel using new parts.
(2) Do the inspections specified in paragraphs (l)(2)(i),
(l)(2)(ii), (l)(2)(iii), and (l)(2)(iv) of this AD and all
applicable corrective actions. Do all applicable corrective actions
before further flight.
(i) A general visual inspection for galling of the fuel supply
manifold assembly;
(ii) A general visual inspection for minimum clearance between
the firewall fuel supply tube assembly and the engine firewall
cutout;
(iii) A general visual inspection for minimum clearance between
the lower nacelle hydraulic tube and hose assemblies; and
(iv) A general visual inspection for minimum clearance between
the lower nacelle fuel tubes and flexible hoses.
(m) For airplanes having serial numbers 45-005 through 45-319,
and 45-321, as identified in Bombardier Service Bulletin 45-71-5,
dated February 13, 2007; and for airplanes having serial numbers 45-
2001 through 45-2069, as identified in Bombardier Service Bulletin
40-71-02, dated February 13, 2007: Before or concurrently with
accomplishing the requirements of paragraph (l) of this AD, do the
applicable actions specified in paragraphs (m)(1), (m)(2), (m)(3),
(m)(4), and (m)(5) of this AD, depending on airplane serial number
and configuration, as specified in, and in accordance with, the
Accomplishment Instructions of Bombardier Service Bulletin 45-71-5
(Model 45, serial numbers 45-005 through 45-319, and 45-321), dated
February 13, 2007; and Bombardier Service Bulletin 40-71-02 (Model
45, serial numbers 45-2001 through 45-2069), dated February 13,
2007; as applicable. Do all applicable corrective actions before
further flight. If, during any inspection required by paragraph
(m)(3), (m)(4), or (m)(5) of this AD, it is determined that
clearances are not met, before further flight, replace the tubing in
accordance with the Accomplishment Instructions of Bombardier
Service Bulletin 45-71-5, dated February 13, 2007; and Bombardier
Service Bulletin 40-71-02, dated February 13, 2007; as applicable.
(1) Change the routing and clamping configuration of the engine
and alternator wire harnesses and the starter/generator wire
bundles.
(2) Do a detailed inspection for chafing damage of specific
hydraulic tubes located within the left engine nacelle between the
adjacent fuel tubes and to determine if there is interference
between the fuel tubing and hydraulic tubing; secure hydraulic tubes
with additional clamps, inspect adjacent fuel tubing for
interference with the hydraulic tubing, replace the left engine
hydraulic pump case drain tube on certain airplanes, and do all
applicable corrective actions.
(3) Do a general visual inspection for clearance between the
left engine hydraulic
[[Page 51705]]
tubing with adjacent tubing, structure, and other components.
(4) Do a general visual inspection for clearance between the
wire harnesses and the hydraulic and fuel tubing on the left engine.
(5) Do a general visual inspection for clearance between the
wire harnesses and the hydraulic and fuel tubing on the right
engine.
Alternative Methods of Compliance (AMOCs)
(n)(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. Send information to
ATTN: James Galstad, Aerospace Engineer, Systems and Propulsion
Branch, ACE-116W, FAA, Wichita ACO, 1801 Airport Road, Room 100,
Mid-Continent Airport, Wichita, Kansas 67209; telephone (316) 946-
4135; fax (316) 946-4107.
(2) To request a different method of compliance or a different
compliance time for this AD, follow the procedures in 14 CFR 39.19.
Before using any approved AMOC on any airplane to which the AMOC
applies, notify your principal maintenance inspector (PMI) or
principal avionics inspector (PAI), as appropriate, or lacking a
principal inspector, your local Flight Standards District Office.
The AMOC approval letter must specifically reference this AD.
(3) AMOCs approved previously in accordance with AD 2009-11-13,
amendment 39-15923, are approved as AMOCs for the corresponding
provisions of this AD.
Issued in Renton, Washington, on August 16, 2010.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2010-20853 Filed 8-20-10; 8:45 am]
BILLING CODE 4910-13-P