[Federal Register Volume 71, Number 198 (Friday, October 13, 2006)]
[Proposed Rules]
[Pages 60450-60454]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: E6-17005]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-26050; Directorate Identifier 2006-NM-078-AD]
RIN 2120-AA64


Airworthiness Directives; Bombardier Model DHC-8-400 Series 
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 Bombardier Model DHC-8-400 
series airplanes. The existing AD currently requires revising the 
airplane flight manual (AFM) to advise the flightcrew of appropriate 
procedures to follow in the event that a main landing gear (MLG) fails 
to extend following a gear-down selection. The existing AD also 
currently requires repetitive replacement of the left and right MLG 
uplock assemblies with new assemblies; and an inspection of the left 
and right MLG uplock rollers for the presence of an inner low friction 
liner, and corrective actions if necessary. This proposed AD would 
revise the requirement for replacing the left and right MLG uplock 
assemblies by allowing replacement with alternative parts. For a 
certain MLG uplock assembly, this proposed AD would require repetitive 
inspections of the uplock hatch lower jaw for the presence of a wear 
groove and replacement with an improved part if necessary. For a 
certain MLG uplock assembly, this proposed AD also would require 
repetitive inspections of the uplock roller to ensure that it rotates 
freely and replacement with a new part if necessary. This proposed AD 
would allow optional replacement of the left and right MLG uplock 
assemblies with improved parts, which ends the requirements of the AFM 
revision and repetitive replacement and inspections. This proposed AD 
would remove airplanes from the applicability. This proposed AD results 
from development of a terminating action. We are proposing this AD to 
ensure that the flightcrew has the procedures necessary to address 
failure of an MLG to extend following a gear-down selection; and to 
detect and correct such failure, which could result in a gear-up 
landing and possible injury to passengers and crew.

DATES: We must receive comments on this proposed AD by November 13, 
2006.

ADDRESSES: Use one of the following addresses to submit comments on 
this proposed AD.
     DOT Docket Web site: Go to http://dms.dot.gov and follow 
the instructions for sending your comments electronically.
     Government-wide rulemaking Web site: Go to http://www.regulations.gov and follow the instructions for sending your 
comments electronically.
     Mail: Docket Management Facility; U.S. Department of 
Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401, 
Washington, DC 20590.
     Fax: (202) 493-2251.
     Hand Delivery: Room PL-401 on the plaza level of the 
Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    Contact Bombardier, Inc., Bombardier Regional Aircraft Division, 
123 Garratt Boulevard, Downsview, Ontario M3K 1Y5, Canada, for service 
information identified in this proposed AD.

FOR FURTHER INFORMATION CONTACT: Ezra Sasson, Aerospace Engineer, 
Systems and Flight Test Branch, ANE-172, FAA, New York Aircraft 
Certification Office, 1600 Stewart Avenue, Suite 410, Westbury, New 
York 11590; telephone (516) 228-7320; fax (516) 794-5531.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to submit any relevant written data, views, or 
arguments regarding this proposed AD. Send your comments to an address 
listed in the ADDRESSES section. Include the docket number ``Docket No. 
FAA-2006-26050; Directorate Identifier 2006-NM-078-AD'' at the 
beginning of your comments. We specifically invite comments on the 
overall regulatory, economic, environmental, and energy aspects of the 
proposed AD. We will consider all comments received by the closing date 
and may amend the proposed AD in light of those comments.
    We will post all comments we receive, without change, to http://dms.dot.gov, including any personal information you provide. We will 
also post a report summarizing each substantive verbal contact with FAA 
personnel concerning this proposed AD. Using the search function of 
that Web site, anyone can find and read the comments in any of our 
dockets, including the name of the individual who sent the comment (or 
signed the comment on behalf of an association, business, labor union, 
etc.). You may review the DOT's complete Privacy Act Statement in the 
Federal Register published on April 11, 2000 (65 FR 19477-78), or you 
may visit http://dms.dot.gov.

Examining the Docket

    You may examine the AD docket on the Internet at http://dms.dot.gov, or in person at the Docket Management Facility office 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The Docket Management Facility office (telephone (800) 647-
5227) is located on the plaza level of the Nassif Building at the DOT 
street address stated in the ADDRESSES section. Comments will be 
available in the AD docket shortly after the Docket Management System 
receives them.

Discussion

    On April 11, 2002, we issued AD 2002-08-05, amendment 39-12713 (67 
FR 19101, April 18, 2002), for certain Bombardier Model DHC-8-400 
series airplanes. That AD requires revising the airplane flight manual 
(AFM) to advise the flightcrew of appropriate procedures to follow in 
the event that a main landing gear (MLG) fails to extend following a 
gear-down selection. That AD also requires repetitive replacement

[[Page 60451]]

of the left and right MLG uplock assemblies (part number (P/N) 46500-3) 
with new assemblies; and an inspection of the left and right MLG uplock 
rollers for the presence of an inner low friction liner, and corrective 
actions if necessary. That AD resulted from an in-flight incident where 
the flightcrew had difficulties in extending the right MLG following a 
gear-down selection. We issued that AD to ensure that the flightcrew 
has the procedures necessary to address failure of an MLG to extend 
following a gear-down selection; and to detect and correct such 
failure, which could result in a gear-up landing and possible injury to 
passengers and crew.

Actions Since Existing AD Was Issued

    In the preamble to AD 2002-08-05, we specified that the actions 
required by that AD were considered ``interim action'' and that the 
manufacturer was developing a modification to address the unsafe 
condition. We indicated that we may consider further rulemaking action 
once the modification was developed, approved, and available. The 
manufacturer now has developed such a modification, and we have 
determined that further rulemaking action is indeed necessary; this 
proposed AD follows from that determination.
    Since we issued AD 2002-08-05, Transport Canada Civil Aviation 
(TCCA), which is the airworthiness authority for Canada, has issued 
Canadian airworthiness directives CF-2002-13R1, dated November 20, 
2002, and CF-2002-13R2, dated May 19, 2005. (Canadian airworthiness 
directive CF-2002-13, dated February 4, 2002, parallels AD 2002-08-05.) 
Canadian airworthiness directive CF-2002-13R1 introduced a new, 
modified uplock assembly, P/N 46500-5, as a replacement alternative to 
P/N 46500-3, which is no longer in production. Canadian airworthiness 
directive CF-2002-13R1 also mandated repetitive replacement of P/N 
46500-5, since it is similar in design to P/N 46500-3 and, therefore, 
subject to the same failure.
    Canadian airworthiness directive CF-2002-13R2 supersedes Canadian 
airworthiness directive CF-2002-13R1. Canadian airworthiness directive 
CF-2002-13R2 revises the requirement for P/N 46500-5 by mandating 
repetitive inspections of P/N 46500-5 and its corresponding uplock 
roller, instead of repetitive replacement. Canadian airworthiness 
directive CF-2002-13R2 also introduces a new, improved uplock assembly, 
P/N 46500-7. The repetitive replacement of P/N 46500-3 and the 
repetitive inspections of P/N 46500-5 and corresponding uplock roller 
are terminated by replacement with P/N 46500-7. Also, Canadian 
airworthiness directive CF-2002-13R2 removes airplanes that have been 
modified in production from the applicability.

Relevant Service Information

    We have reviewed Bombardier Temporary Revision (TR) 32-191 and TR 
32-192, both dated May 29, 2006, to the Bombardier Q400 Dash 8 Aircraft 
Maintenance Manual (AMM), PSM 1-84-2. TR 32-191 describes procedures 
for removing an uplock roller from the MLG uplock assembly. TR 32-192 
describes procedures for installing an uplock roller in the MLG uplock 
assembly.
    TCCA issued Canadian airworthiness directive CF-2002-13R2, dated 
May 19, 2005, to ensure the continued airworthiness of these airplanes 
in Canada.

FAA's Determination and Requirements of the Proposed AD

    This airplane model is manufactured in Canada and is type 
certificated for operation in the United States under the provisions of 
section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and 
the applicable bilateral airworthiness agreement. Pursuant to this 
bilateral airworthiness agreement, TCCA has kept the FAA informed of 
the situation described above. We have examined TCCA's findings, 
evaluated all pertinent information, and determined that AD action is 
necessary for airplanes of this type design that are certificated for 
operation in the United States.
    This proposed AD would supersede AD 2002-08-05 and would retain the 
requirements of the existing AD; except that this proposed AD would 
revise the requirement for replacing the left and right MLG uplock 
assemblies by allowing replacement with modified or improved uplock 
assemblies, P/N 46500-5 or -7, respectively. This proposed AD would 
also require the following actions:
     For MLG uplock assembly, P/N 46500-5: Repetitive detailed 
dimensional inspections of the surface of the uplock hatch lower jaw of 
the MLG uplock assembly for the presence of a wear groove and 
replacement of the uplock assembly with an improved uplock assembly, P/
N 46500-7, if necessary.
     For MLG uplock assembly, P/N 46500-5: Repetitive general 
visual inspections of the uplock roller of the MLG uplock assembly to 
ensure that it rotates freely and replacement of the uplock roller with 
a new uplock roller if necessary.
    Also, this proposed AD would allow optional replacement of the left 
and right MLG uplock assemblies with improved uplock assemblies, P/N 
46500-7, which ends the requirements of the AFM revision and repetitive 
replacement and inspections. This proposed AD also would remove 
airplanes from the applicability.

Difference Between the Proposed AD and Canadian Airworthiness Directive

    Canadian airworthiness directive CF-2002-13R2 specifies replacing 
the uplock roller of a certain MLG uplock assembly in accordance with 
Chapter 32-31-21 of the Bombardier Q400 Dash 8 AMM, PSM 1-84-2, if the 
uplock roller does not rotate freely. However, Chapter 32-31-21, 
Revision 20, dated May 5, 2005, of the Bombardier Q400 Dash 8 AMM does 
not include a procedure for accomplishing the replacement. Therefore, 
this proposed AD would require accomplishing the replacement in 
accordance with Bombardier TR 32-191 and TR 32-192. We have coordinated 
this difference with TCCA and Bombardier.

Clarification of Compliance Time

    Canadian airworthiness directive CF-2002-13R2 specifies replacing 
the MLG uplock assembly if the wear groove depth of the uplock latch 
lower jaw exceeds 0.007 inch (in paragraph C.1.). Canadian 
airworthiness directive CF-2002-13R2 also specifies replacing the 
uplock roller if it does not rotate freely (in paragraph C.2.). 
However, in both cases, Canadian airworthiness directive CF-2002-13R2 
does not explicitly specify the compliance time for accomplishing these 
actions. This proposed AD would require accomplishing these actions 
before further flight.

Clarification of Inspection Terminology

    The ``inspection'' of the uplock roller specified in Canadian 
airworthiness directive CF-2002-13R2 is referred to as a ``general 
visual inspection'' in this proposed AD. We have included the 
definition for a general visual inspection as a note in the proposed 
AD.

Change to Existing AD

    This proposed AD would retain all requirements of AD 2002-08-05. 
Since AD 2002-08-05 was issued, the AD format has been revised, and 
certain paragraphs have been rearranged. As a result, the corresponding 
paragraph identifiers have changed in this proposed AD, as listed in 
the following table:

[[Page 60452]]



                      Revised Paragraph Identifiers
------------------------------------------------------------------------
                                             Corresponding  requirement
       Requirement in  AD 2002-08-05            in this  proposed AD
------------------------------------------------------------------------
paragraph (a).............................  paragraph (f).
paragraph (b).............................  paragraph (g).
paragraph (c).............................  paragraph (h).
------------------------------------------------------------------------

    Note 2 of AD 2002-08-05 was inadvertently misplaced in paragraph 
(b)(2) instead of paragraph (c)(2) of the existing AD. Accordingly, we 
have moved Note 2 to paragraph (h)(2) in this proposed AD.
    Paragraph (c)(2) of AD 2002-08-05 (corresponding to paragraph 
(h)(2) of this proposed AD) requires replacing an uplock roller if a 
low friction liner is not present, in accordance with the 
Accomplishment Instructions of Bombardier DHC-8 Alert Service Bulletin 
A84-32-15, dated February 4, 2002. After the effective date of this AD, 
if the low friction liner is not present, operators must accomplish the 
replacement in accordance with paragraph (i)(2) of this proposed AD. We 
have revised paragraph (h)(2) of this proposed AD accordingly.

Explanation of Change to Applicability

    We have revised the applicability of the proposed AD to identify 
model designations as published in the most recent type certificate 
data sheet for the affected models.

Costs of Compliance

    The following table provides the estimated costs, at an average 
labor rate of $80 per work hour, for U.S. operators to comply with this 
proposed AD.

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                Number of U.S.-
            Action                 Work          Parts            Cost per        registered       Fleet cost
                                  hours                           airplane         airplanes
----------------------------------------------------------------------------------------------------------------
AFM revision (required by AD            1  None.............  $80.............              21  $1,680.
 2002-08-05).
Replacement of uplock                   4  No charge........  $320, per                     21  $6,720 per
 assemblies (required by AD                                    replacement                       replacement
 2002-08-05).                                                  cycle.                            cycle.
Inspection of uplock rollers            1  None.............  $80.............              21  $1,680.
 (required by AD 2002-08-05).
Inspections of uplock                   5  None.............  $400............              21  $8,400.
 assemblies and uplock rollers
 (new proposed action).
Terminating action (new                 4  No charge........  $320............              21  $6,720.
 proposed action).
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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, 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 Federal Aviation Administration (FAA) amends Sec.  39.13 by 
removing amendment 39-12713 (67 FR 19101, April 18, 2002) and adding 
the following new airworthiness directive (AD):

Bombardier, Inc. (Formerly de Havilland, Inc.): Docket No. FAA-2006-
26050; Directorate Identifier 2006-NM-078-AD.

Comments Due Date

    (a) The FAA must receive comments on this AD action by November 
13, 2006.

Affected ADs

    (b) This AD supersedes AD 2002-08-05.

Applicability

    (c) This AD applies to Bombardier Model DHC-8-400 series 
airplanes, certificated in any category; serial numbers 4001 and 
4003 through 4087 inclusive; equipped with main landing gear (MLG) 
uplock assembly part numbers (P/Ns) 46500-3 and -5.

Unsafe Condition

    (d) This AD results from development of a terminating action. We 
are issuing this AD to ensure that the flightcrew has the procedures 
necessary to address failure of an MLG to extend following a gear-
down selection; and to detect and correct such failure, which could 
result in a gear-up landing and possible injury to passengers and 
crew.

Compliance

    (e) You are responsible for having the actions required by this 
AD performed within the compliance times specified, unless the 
actions have already been done.

Requirements of AD 2002-08-05

Revision of FAA-Approved Airplane Flight Manual (AFM)

    (f) Within 3 days after April 23, 2002 (the effective date of AD 
2002-08-05), amend all

[[Page 60453]]

copies of the FAA-approved Bombardier Series 400 AFM, PSM 1-84-1A 
(for Models 400, 401, and 402), by adding the following procedure to 
the Limitations section of the AFM and opposite page 4-21-1 of the 
AFM; and advise all flightcrew members of these changes. (The 
revision may be accomplished by inserting a copy of this AD into the 
Limitations section of the AFM and affected paragraphs of the AFM.):
    ``If ONE main landing gear fails to extend after performing 
landing gear extension per normal procedures given in paragraph 
4.3.7 and alternate extension procedures per paragraph 4.21.1 of the 
AFM:
    1. Visually confirm that the affected gear has not extended and 
that the associated doors have opened.
    2. Ensure No. 2 hydraulic system pressure and quantity are 
normal and the following landing gear advisory lights are 
illuminated: selector lever amber, gear green locked down (nose and 
non-affected main gear), red gear unlocked (affected main gear) and 
all amber doors open.
    3. NOSE L/G RELEASE handle--Return to the stowed position.
    4. LANDING GEAR ALTERNATE EXTENSION door--Close fully.
    5. MAIN L/G RELEASE handle--Return to the stowed position.
    6. LANDING GEAR ALTERNATE RELEASE door--Close fully.
    7. LANDING GEAR lever--DN.
    8. L/G DOWN SELECT INHIBIT SW--Normal and guarded. Check amber 
doors open advisory lights out (nose and non-affected main gear) and 
LDG GEAR INOP caution light out.
    9. LANDING GEAR lever--UP Check all gear, door and LANDING GEAR 
lever advisory lights out.
    10. With minimum delay, LANDING GEAR lever--DN. Check 3 green 
gear locked down advisory lights illuminate, all amber doors open, 
red gear unlocked and selector lever amber advisory lights out.
    11. Items 9 and 10 may be repeated in an effort to achieve 3 
gear down and locked.

CAUTION

    Should the LDG GEAR INOP caution light illuminate, or loss of 
no. 2 hydraulic system pressure or quantity, or any abnormality in 
landing gear system indication other than those associated with the 
affected main landing gear be experienced, see paragraph 4.21.1 
ALTERNATE LANDING GEAR EXTENSION.''
    Accomplishing the actions specified in paragraph (k) of this AD 
terminates the requirements of this paragraph, and after the 
replacement has been done, the AFM limitation may be removed from 
the AFM.

Replacement of Uplock Assembly with New Replacement Parts and 
Requirements

    (g) At the later of the times specified in paragraph (g)(1) or 
(g)(2) of this AD: Replace the left and right MLG uplock assemblies, 
P/N 46500-3, with new or overhauled uplock assemblies having P/N 
46500-3, -5, or -7, according to a method approved by either the 
Manager, New York Aircraft Certification Office (ACO), FAA; or 
Transport Canada Civil Aviation (TCCA) (or its delegated agent). 
Using Tasks 32-31-21-000-801 and 32-31-21-400-801 of Chapter 32-31-
21 of Bombardier Q400 Dash 8 Aircraft Maintenance Manual (AMM), PSM 
1-84-2, is one approved method. For any uplock assembly having P/N 
46500-3, repeat the replacement thereafter at intervals not to 
exceed 2,500 flight hours or 3,000 flight cycles, whichever occurs 
earlier. For any uplock assembly having P/N 46500-5, do the actions 
required by paragraph (i) of this AD. Replacing an uplock assembly 
with a new or overhauled uplock assembly having P/N 46500-7 
terminates the requirements of this paragraph, for that uplock 
assembly only.
    (1) Before the accumulation of 2,500 total flight hours or 3,000 
total flight cycles on an uplock assembly, whichever occurs earlier; 
or
    (2) Within 14 days after April 23, 2002.

One-Time Inspection of MLG Uplock Rollers With Added Inspection 
Definition

    (h) Within 30 days after April 23, 2002, do a general visual 
inspection of the left and right MLG uplock rollers for the presence 
of an inner low friction (black-colored) liner, in accordance with 
the Accomplishment Instructions of Bombardier DHC-8 Alert Service 
Bulletin A84-32-15, dated February 4, 2002; and, before further 
flight, do the actions required by paragraph (h)(1) or (h)(2) of 
this AD.

    Note 1: For the purposes of this AD, a general visual inspection 
is: ``A visual examination of an interior or exterior area, 
installation, or assembly to detect obvious damage, failure, or 
irregularity. This level of inspection is made from within touching 
distance unless otherwise specified. A mirror may be necessary to 
ensure visual access to all surfaces in the inspection area. This 
level of inspection is made under normally available lighting 
conditions such as daylight, hangar lighting, flashlight, or 
droplight and may require removal or opening of access panels or 
doors. Stands, ladders, or platforms may be required to gain 
proximity to the area being checked.''

Corrective Actions

    (1) If a low friction liner is present, reinstall the existing 
uplock roller; or install a new uplock roller, P/N 46575-1, having a 
low friction liner; on the shock strut of the MLG in accordance with 
the service bulletin.
    (2) If a low friction liner is not present, replace the existing 
uplock roller with a new uplock roller, P/N 46575-1, having a low 
friction liner, on the shock strut of the MLG in accordance with the 
service bulletin. After the effective date of this AD, if the low 
friction liner is not present, replace the uplock roller in 
accordance with paragraph (i)(2) of this AD.

    Note 2: Bombardier DHC-8 Alert Service Bulletin A84-32-15, dated 
February 4, 2002, references Chapter 32-11-01 of Bombardier Q400 
Dash 8 AMM, PSM 1-84-2, as an additional source of service 
information for procedures to replace an MLG uplock roller.

New Requirements of This AD

Repetitive Inspections and Replacement if Necessary of a Certain 
Uplock Assembly

    (i) For any MLG uplock assembly having P/N 46500-5, do the 
inspections specified in paragraphs (i)(1) and (i)(2) of this AD at 
the later of the following compliance times: Before the accumulation 
of 2,500 total flight hours or 3,000 total flight cycles on the 
uplock assembly, whichever occurs first; or within 90 days after the 
effective date of this AD. Repeat the inspections thereafter at 
intervals not to exceed 400 total flight hours or 480 total flight 
cycles, whichever occurs first. Replacement of an uplock assembly in 
accordance with paragraph (i)(1) of this AD terminates the 
repetitive inspections of paragraphs (i)(1) and (i)(2) of this AD, 
for that uplock assembly only.
    (1) Do a detailed dimensional inspection of the surface of the 
uplock hatch lower jaw for the presence of a wear groove and measure 
the wear groove depth to an accuracy of 0.001 inch, according to a 
method approved by either the Manager, New York ACO; or TCCA (or its 
delegated agent). Using Task 32-31-21-220-801 of the Bombardier Q400 
Dash 8 AMM, PSM 1-84-2, is one approved method. If the groove depth 
exceeds 0.007 inch, before further flight, replace the uplock 
assembly with a new or serviceable uplock assembly, P/N 46500-7, 
according to a method approved by either the Manager, New York ACO; 
or TCCA (or its delegated agent). Using Tasks 32-31-21-000-801 and 
32-31-21-400-801 of Chapter 32-31-21 of the Bombardier Q400 Dash 8 
AMM, PSM 1-84-2, is one approved method.
    (2) Do a general visual inspection of the uplock roller, P/N 
46575-1, of the MLG uplock assembly to ensure that it rotates 
freely. If the uplock roller does not rotate freely, before further 
flight, replace the uplock roller with a new uplock roller, P/N 
46575-1, in accordance with Bombardier Temporary Revision (TR) 32-
191 and Bombardier TR 32-192, both dated May 29, 2006.
    (j) When the information in Bombardier TR 32-191 and Bombardier 
TR 32-192, both dated May 29, 2006, is included in the AMM, the AMM 
is approved as an acceptable method of compliance for the 
replacement specified paragraph (i)(2) of this AD.

Optional Terminating Action for AFM Revision, Repetitive 
Replacements, and Repetitive Inspections

    (k) Replacing the left and right MLG uplock assemblies having P/
N 46500-3 or -5 with new or overhauled uplock assemblies having P/N 
46500-7 terminates the requirements of paragraphs (f), (g), (h), and 
(i) of this AD, as applicable. After the replacements have been 
done, the AFM limitation required by paragraph (f) of this AD may be 
removed from the AFM.

Alternative Methods of Compliance (AMOCs)

    (l)(1) The Manager, New York ACO, has the authority to approve 
AMOCs for this AD, if requested in accordance with the procedures 
found in 14 CFR 39.19.
    (2) Before using any AMOC approved in accordance with Sec.  
39.19 on any airplane to which the AMOC applies, notify the

[[Page 60454]]

appropriate principal inspector in the FAA Flight Standards 
Certificate Holding District Office.
    (3) AMOCs approved previously in accordance with AD 2002-08-05, 
are approved as AMOCs for the corresponding provisions of this AD.

Related Information

    (m) Canadian airworthiness directive CF-2002-13R2, dated May 19, 
2005, also addresses the subject of this AD.

    Issued in Renton, Washington, on October 3, 2006.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
 [FR Doc. E6-17005 Filed 10-12-06; 8:45 am]
BILLING CODE 4910-13-P