AD 2011-17-17

[Federal Register Volume 76, Number 177 (Tuesday, September 13, 2011)]
[Rules and Regulations]
[Pages 56290-56294]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2011-22468]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2011-0151; Directorate Identifier 2009-NM-205-AD; 
Amendment 39-16781; AD 2011-17-17]
RIN 2120-AA64


Airworthiness Directives; Bombardier, Inc. Model DHC-8-400 Series 
Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule.

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SUMMARY: We are superseding an existing airworthiness directive (AD) 
that applies to the products listed above. This AD results from 
mandatory continuing airworthiness information (MCAI) originated by an 
aviation authority of another country to identify and correct an unsafe 
condition on an aviation product. The MCAI describes the unsafe 
condition as:

    Two cases of main landing gear collapse had been reported. Main 
landing gear collapse may result in unsafe landing of the aircraft.
* * * * *
We are issuing this AD to require actions to correct the unsafe 
condition on these products.

DATES: This AD becomes effective October 18, 2011.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of October 18, 
2011.

ADDRESSES: You may examine the AD docket on the Internet at <a href="http://www.regulations.gov">http://www.regulations.gov</a> or in person at the U.S. Department of 
Transportation, Docket Operations, M-30, West Building Ground Floor, 
Room W12-140, 1200 New Jersey Avenue, SE., Washington, DC.

FOR FURTHER INFORMATION CONTACT: Craig Yates, Aerospace Engineer, 
Airframe and Mechanical Systems Branch, ANE-171, FAA, New York Aircraft 
Certification Office (ACO), 1600 Stewart Avenue, Suite 410, Westbury, 
New York 11590; telephone (516) 228-7355; fax (516) 794-5531.

SUPPLEMENTARY INFORMATION:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to include an AD that would apply to the specified products. 
That NPRM was published in the Federal Register on March 8, 2011 (76 FR 
12629), and proposed to supersede AD 2007-22-09, Amendment 39-15245 (72 
FR 61288, October 30, 2007). That NPRM proposed to correct an unsafe 
condition for the specified products. The MCAI states:

    Two cases of main landing gear collapse had been reported. Main 
landing gear collapse may result in unsafe landing of the aircraft.
    Revision 1 of this directive amended the time compliance in 
paragraph C.2 (3 months in addition to 500 hours air time), to add 
new paragraph C.3 to cater for retract actuator which has 
accumulated less than 4,000 landings or 2 years since new and to add 
new paragraphs B.2 and C.4 to require that the respective 
inspections be repetitively performed until terminating action 
becomes available.
    Revision 2 of this directive amends the detailed visual 
inspection requirement in paragraph C.3 to include the main landing 
gear retract actuator, part number 46550-11, and to add new 
paragraph F to mandate the incorporation of main landing gear 
retract actuator part number, 46550-13 as the terminating action and 
to add new paragraph G for the maintenance requirement.

You may obtain further information by examining the MCAI in the AD 
docket.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We received no comments on the NPRM (76 FR 12629, March 8, 
2011) or on the determination of the cost to the public.

Change Made to This AD

    We have removed paragraph (v)(3)(i)(D) of the NPRM (76 FR 12629, 
March 8, 2011) from this AD, and reidentified subsequent paragraphs 
accordingly.

Conclusion

    We reviewed the available data, and determined that air safety and 
the public interest require adopting the AD with the change described 
previously. We determined that this change will not increase the 
economic burden on any operator or increase the scope of the AD.

Differences Between This AD and the MCAI or Service Information

    We have reviewed the MCAI and related service information and, in 
general, agree with their substance. But we might have found it 
necessary to use different words from those in the MCAI to ensure the 
AD is clear for U.S. operators and is enforceable. In making these 
changes, we do not intend to differ substantively from the information 
provided in the MCAI and related service information.
    We might also have required different actions in this AD from those 
in the MCAI in order to follow our FAA

[[Page 56291]]

policies. Any such differences are highlighted in a Note within the AD.

Costs of Compliance

    We estimate that this AD will affect about 55 products of U.S. 
registry.
    The actions that are required by AD 2007-22-09, Amendment 39-15245 
(72 FR 61288, October 30, 2007), and retained in this AD take about 5 
work-hours per product, at an average labor rate of $85 per work-hour. 
Based on these figures, the estimated cost of the currently required 
actions is $425 per product.
    We estimate that it will take about 8 work-hours per product to 
comply with the new basic requirements of this AD. The average labor 
rate is $85 per work-hour. Required parts will cost about $27,511 per 
product. Where the service information lists required parts costs that 
are covered under warranty, we have assumed that there will be no 
charge for these parts. As we do not control warranty coverage for 
affected parties, some parties may incur costs higher than estimated 
here. Based on these figures, we estimate the cost of this AD to the 
U.S. operators to be $1,550,505, or $28,191 per product.

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 determined that this AD will not have federalism implications 
under Executive Order 13132. This AD will not have a substantial direct 
effect on the States, on the relationship between the national 
government and the States, or on the distribution of power and 
responsibilities among the various levels of government.
    For the reasons discussed above, I certify this AD:
    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 AD and placed it in the AD docket.

Examining the AD Docket

    You may examine the AD docket on the Internet at <a href="http://www.regulations.gov">http://www.regulations.gov</a>; or in person at the Docket Operations office 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The AD docket contains the NPRM (76 FR 12629, March 8, 2011), 
the regulatory evaluation, any comments received, and other 
information. The street address for the Docket Operations office 
(telephone (800) 647-5527) is in the ADDRESSES section. Comments will 
be available in the AD docket shortly after receipt.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority: 49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by removing Amendment 39-15245 (72 FR 
61288, October 30, 2007) and adding the following new AD:

2011-17-17 Bombardier, Inc.: Amendment 39-16781. Docket No. FAA-
2011-0151; Directorate Identifier 2009-NM-205-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective October 
18, 2011.

Affected ADs

    (b) This AD supersedes AD 2007-22-09, Amendment 39-15245 (72 FR 
61288, October 30, 2007).

Applicability

    (c) This AD applies to Bombardier, Inc. Model DHC-8-400, -401, 
and -402 airplanes, certificated in any category, having serial 
numbers (S/Ns) 4001, 4003, 4004, 4006, and 4008 through 4208 
inclusive.

Subject

    (d) Air Transport Association (ATA) of America Code 32: Landing 
Gear.

Reason

    (e) The mandatory continuing airworthiness information (MCAI) 
states:

    Two cases of main landing gear collapse had been reported. Main 
landing gear collapse may result in unsafe landing of the aircraft.
* * * * *

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 2007-22-09, Amendment 39-15245 (72 FR 
61288, October 30, 2007), With Updated Service Information, Limited 
Affected Airplanes, and Revised Compliance Times

General Visual Inspection of Main Landing Gear (MLG) System, and 
Corrective Actions

    (g) For airplanes having S/Ns 003, 004, 006, and 008 through 182 
inclusive (now referred to as S/Ns 4003, 4004, 4006, and 4008 
through 4182 inclusive), before further flight, do a general visual 
inspection to detect discrepancies of the left- and right-hand MLG 
system and do all applicable corrective actions, in accordance with 
a method approved by the Manager, New York Aircraft Certification 
Office (ACO), FAA; or Transport Canada Civil Aviation (TCCA) (or its 
delegated agent).

    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.''


    Note 2: Guidance on doing a general visual inspection to detect 
discrepancies of the left- and right-hand MLG system can be found in 
Tasks Z700-03E and Z700-04E of Part 1 (Maintenance Review Board 
Report) of the Bombardier DHC-8 Series 400 Maintenance Requirements 
Manual (PSM 1-84-7).

General Visual Inspection of the Jam Nut of the Retract Actuator of 
the MLG and Corrective Actions

    (h) For all airplanes except for the airplane having serial 
number 4001: Before further flight, do a general visual inspection 
of the jam nut of the retract actuator of the left- and right-hand 
MLG to ensure the wire lock is in place and the nut is secured. If 
the wire lock is not in place or if the jam nut is not

[[Page 56292]]

secured, before further flight, adjust the retracted length of the 
rod end, torque the jam nut, install a wire lock, and lubricate the 
piston, as applicable, in accordance with Bombardier Repair Drawing 
(RD) 8/4-32-059, Issue 4, dated September 14, 2007; or Issue 7, 
dated June 26, 2008. As of the effective date of this AD, use only 
Bombardier RD 8/4-32-059, Issue 7, dated June 26, 2008. Doing the 
revision required by paragraph (r) of this AD terminates the 
inspection required by this paragraph.

    Note 3: Bombardier RD 8/4-32-059, Issue 4, dated September 14, 
2007, refers to Goodrich Service Concession Request SCR 086-07, 
Revision C, dated September 14, 2007 (specifically item 14); and 
Bombardier RD 8/4-32-059, Issue 7, dated June 26, 2008, refers to 
Goodrich Service Concession Request SCR 086-07, Revision F, dated 
June 13, 2008 (specifically item 14); as an additional source of 
service information for adjusting the retracted length of the rod 
end, torquing the jam nut, installing a wire lock, and lubricating 
the piston if necessary, as required by paragraph (h) of this AD.

Detailed Inspection of the Retract Actuator of the MLG, With 
Extended Compliance Time for Paragraph (j) of This AD

    (i) For airplanes having S/Ns 003, 004, 006, and 008 through 182 
inclusive (now referred to as S/Ns 4003, 4004, 4006, and 4008 
through 4182 inclusive) on which the retract actuator of the MLG, 
part number (P/N) 46550-7 or 46550-9, has accumulated 8,000 or more 
total landings or has been in-service 4 or more years since new, as 
of November 14, 2007 (the effective date of AD 2007-22-09, Amendment 
39-15245 (72 FR 61288, October 30, 2007)): Before further flight, do 
a detailed inspection of affected parts for any signs of corrosion 
or wear, and applicable related investigative and corrective 
actions, in accordance with Bombardier RD 8/4-32-059, Issue 4, dated 
September 14, 2007; or Issue 7, dated June 26, 2008. As of the 
effective date of this AD, use only Bombardier RD 8/4-32-059, Issue 
7, dated June 26, 2008.

    Note 4: 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.''

    (j) For airplanes having S/Ns 003, 004, 006, and 008 through 182 
inclusive (now referred to as S/Ns 4003, 4004, 4006, and 4008 
through 4182 inclusive) with a retract actuator of the MLG, P/N 
46550-7 or 46550-9, other than those identified in paragraph (i) of 
this AD: Do a detailed inspection of affected parts for any signs of 
corrosion or wear, and applicable related investigative and 
corrective actions, in accordance with Bombardier RD 8/4-32-059, 
Issue 4, dated September 14, 2007; or Issue 7, dated June 26, 2008; 
at the later of the times specified in paragraphs (j)(1) and (j)(2) 
of this AD. As of the effective date of this AD, use only Bombardier 
RD 8/4-32-059, Issue 7, dated June 26, 2008.
    (1) Before the accumulation of 4,500 total landings or 27 months 
since new, whichever occurs first.
    (2) Within 500 flight hours after November 14, 2007, or within 3 
months after the effective date of this AD, whichever occurs first.

    Note 5: Bombardier RD 8/4-32-059, Issue 7, dated June 26, 2008, 
refers to Goodrich Service Concession Request SCR 086-07, Revision 
F, dated June 13, 2008, as an additional source of service 
information for accomplishing the applicable related investigative 
and corrective actions required by paragraphs (i) and (j) of this 
AD.

Actions Done in Accordance With Previous Issues of Service 
Information

    (k) Actions done before November 14, 2007, in accordance with 
repair drawings specified in Table 1 of this AD, are acceptable for 
compliance with the corresponding actions specified in paragraphs 
(h) through (j) of this AD.

                    Table 1--Previous Repair Drawings
------------------------------------------------------------------------
            Document               Issue                Date
------------------------------------------------------------------------
Bombardier Repair Drawing 8/4-          1  September 12, 2007.
 32-059.
Bombardier Repair Drawing 8/4-          2  September 13, 2007.
 32-059.
Bombardier Repair Drawing 8/4-          3  September 13, 2007.
 32-059.
------------------------------------------------------------------------

New Requirements of This AD

General Visual Inspection of the Jam Nut of the Retract Actuator of 
the MLG, and Corrective Actions

    (l) For all airplanes: At the later of the times specified in 
paragraphs (l)(1) and (l)(2) of this AD, do a general visual 
inspection of the left- and right-hand MLG retract actuator jam nut 
to ensure that the wire lock is in place and that the nut is secure, 
in accordance with a method approved by the Manager, New York ACO, 
FAA; or TCCA (or its delegated agent). If the wire lock is not in 
place or the jam nut is not secured, before further flight, re-
torque the jam nut and safety lockwire, in accordance with 
Bombardier RD 8/4-32-059, Issue 7, dated June 26, 2008. Repeat the 
inspection thereafter at intervals not to exceed 250 flight cycles 
or 30 days, whichever occurs first. Doing the revision required by 
paragraph (r) of this AD terminates the inspections required by this 
paragraph.
    (1) Within 250 flight cycles or 30 days after accomplishing the 
inspection required by paragraph (h) of this AD, whichever occurs 
first.
    (2) Within 7 days after the effective date of this AD.

    Note 6: Guidance for doing a general visual inspection to detect 
discrepancies of the left- and right-hand MLG system can be found in 
Tasks Z700-03E and Z700-04E of Part 1 (Maintenance Review Board 
Report) of the Bombardier DHC-8 Series 400 Maintenance Requirements 
Manual (PSM 1-84-7).

Detailed Inspection of the Retract Actuator of the MLG, and Related 
Investigative and Corrective Actions

    (m) For airplanes equipped with a MLG retract actuator having P/
N 46550-7 or 46550-9: At the later of the times specified in 
paragraphs (m)(1) and (m)(2) of this AD, do a detailed inspection of 
affected parts for any signs of corrosion or wear, and do applicable 
related investigative and corrective actions, in accordance with 
Bombardier RD 8/4-32-059, Issue 7, dated June 26, 2008. Do all 
applicable related investigative and corrective actions before 
further flight. Repeat the inspection thereafter at intervals not to 
exceed 2,000 flight cycles or 12 months, whichever occurs first.
    (1) Within 2,000 flight cycles or within 12 months after 
accomplishing the inspection required by paragraph (i) or (j) of 
this AD, whichever occurs first.
    (2) Within 30 days after the effective date of this AD.
    (n) For airplanes having serial numbers 4001, 4003, 4004, 4006, 
and 4008 through 4182 inclusive equipped with a MLG retract actuator 
having P/N 46550-11: At the later of the times specified in 
paragraphs (n)(1) and (n)(2) of this AD, do a detailed inspection of 
affected parts for any signs of corrosion or wear, and applicable 
related investigative and corrective actions, in accordance with 
Bombardier RD 8/4-32-059, Issue 7, dated June 26, 2008. Do all 
applicable related investigative and corrective actions before 
further flight. Repeat the inspection thereafter at intervals not to 
exceed 2,000 flight cycles or 12 months, whichever occurs first.
    (1) Before the accumulation of 4,500 total landings or 27 months 
since new, whichever occurs first.
    (2) Within 500 flight hours or 3 months after the effective date 
of this AD, whichever occurs first.
    (o) For airplanes having serial numbers 4001, 4003, 4004, 4006, 
and 4008 through 4182 inclusive equipped with a MLG retract actuator 
having P/N 46550-7, P/N 46550-9, or P/N 46550-11, and that have 
accumulated 7,500 total flight cycles or more as of the effective 
date of this AD, or that have more

[[Page 56293]]

than 48 months since new: Within 500 flight cycles or 3 months after 
the effective date of this AD, whichever occurs first, replace the 
affected retract actuator with a new design retract actuator having 
P/N 46550-13, in accordance with Bombardier Service Bulletin 84-32-
55, Revision A, dated March 10, 2008 (Bombardier Modsum 4-901603). 
Doing the replacement specified in this paragraph terminates the 
requirements of paragraphs (i), (j), (m), and (n) of this AD.
    (p) For airplanes having serial numbers 4001, 4003, 4004, 4006, 
and 4008 through 4182 inclusive equipped with MLG retract actuators 
having P/N 46550-7, P/N 46550-9, or P/N 46550-11, that have 
accumulated less than 7,500 total flight cycles as of the effective 
date of this AD and that have 48 months or less since new: Prior to 
the accumulation of 8,000 total flight cycles, or within 51 months 
since new, whichever occurs first, replace the affected retract 
actuator with a new design retract actuator having P/N 46550-13, in 
accordance with Bombardier Service Bulletin 84-32-55, Revision A, 
dated March 10, 2008 (Bombardier Modsum 4-901603). Doing the 
replacement specified in this paragraph terminates the requirements 
of paragraphs (i), (j), (m), and (n) of this AD.
    (q) Replacing the affected retract actuator with a new design 
retract actuator having P/N 46550-15, in accordance with the 
Accomplishment Instructions of Bombardier Service Bulletin 84-32-60, 
Revision A, dated September 29, 2008 (Bombardier Modsum 4-901610), 
is also acceptable for compliance with the requirements of 
paragraphs (o) and (p) of this AD.

Revision of the Maintenance Program

    (r) For all airplanes: Within 30 days after the effective date 
of this AD, revise the maintenance program by incorporating Task 
320100-211 (repetitive detailed inspections of the retraction 
actuator rod end jam nut, gland nut, and actuator attachment pins 
for condition, the security of installation, and corrosion) and Task 
320100-212 (repetitive restorations of the retraction actuator for 
complete overhaul), as specified in Bombardier Temporary Revision 
(TR) MRB-35, dated November 18, 2008, to the Bombardier Q400 Dash 8 
Maintenance Requirements Manual (PSM 1-84-7). Doing this revision 
terminates the requirements of paragraphs (h) and (l) of this AD. 
The initial compliance times for doing Task 320100-211 and Task 
320100-212 are specified in paragraphs (r)(1) and (r)(2) of this AD. 
After doing this revision, no alternative inspections, restorations, 
or intervals may be used, unless the inspections, restorations, or 
intervals are approved as an alternative method of compliance (AMOC) 
in accordance with the procedures specified in paragraph (v)(1) of 
this AD.
    (1) For Task 320100-211 in Bombardier TR MRB-35, dated November 
18, 2008, to the Bombardier Q400 Dash 8 Maintenance Requirements 
Manual (PSM 1-84-7): The compliance time for the initial inspection 
is within 600 flight hours after the effective date of this AD.
    (2) For Task 320100-212 in Bombardier TR MRB-35, dated November 
18, 2008, to the Bombardier Q400 Dash 8 Maintenance Requirements 
Manual (PSM 1-84-7): The compliance time for the initial restoration 
is the later of the times of paragraphs (r)(2)(i) and (r)(2)(ii) of 
this AD.
    (i) Prior to the accumulation of 25,000 total flight cycles, or 
within 12 years since the date of issuance of the original 
airworthiness certificate or the date of issuance of the original 
export certificate of airworthiness, whichever occurs first.
    (ii) Within 500 flight cycles after the effective date of this 
AD.

    Note 7: The actions required by paragraph (r) of this AD may be 
done by inserting copies of Bombardier TR MRB-35, dated November 18, 
2008, into the Bombardier Q400 Dash 8 Maintenance Requirements 
Manual (PSM 1-84-7). When this TR has been included in general 
revisions of the PSM, the general revisions may be inserted in the 
PSM, provided the relevant information in the general revision is 
identical to that in Bombardier TR MRB-35, dated November 18, 2008.

Credit for Actions Accomplished in Accordance With Previous Service 
Information

    (s) Doing a general visual inspection of the jam nut of the 
retract actuator of the left- and right-hand MLG; and doing a 
detailed inspection of affected parts for any signs of corrosion or 
wear, and applicable related investigative and corrective actions; 
is also acceptable for compliance with the corresponding 
requirements of paragraphs (h), (i), (j), (l), (m), and (n) of this 
AD, if done before the effective date of this AD in accordance with 
Bombardier Repair Drawing 8/4-32-059, Issue 5, dated September 20, 
2007; or Bombardier Repair Drawing 8/4-32-059, Issue 6, dated 
January 31, 2008.
    (t) Replacing the affected retract actuator with a new design 
retract actuator having P/N 46550-13 is also acceptable for 
compliance with the requirements of paragraphs (o) and (p) of this 
AD, if done before the effective date of this AD in accordance with 
Bombardier Service Bulletin 84-32-55, dated January 14, 2008 (Modsum 
4-901603).

No Reporting

    (u) While Canadian Airworthiness Directive CF-2007-20R2, dated 
February 6, 2009, has a reporting action, this AD does not require 
reporting.

FAA AD Differences

    Note 8: This AD differs from the MCAI and/or service information 
as follows: Although the MCAI or service information tells you to 
submit information to the manufacturer, paragraph (u) of this AD 
specifies that such submittal is not required.

Other FAA AD Provisions

    (v) The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, New 
York Aircraft Certification Office (ACO), ANE-170, 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 ACO, send it to ATTN: Program Manager, Continuing 
Operational Safety, FAA, New York ACO, 1600 Stewart Avenue, Suite 
410, Westbury, New York 11590; telephone 516-228-7300; fax 516-794-
5531. 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. The AMOC approval letter must specifically 
reference this AD. AMOCs approved previously in accordance with AD 
2007-22-09, Amendment 39-15245 (72 FR 61288, October 30, 2007), are 
approved as AMOCs for the corresponding provisions of paragraph (i) 
and (j) of this AD.
    (2) Airworthy Product: For any requirement in this AD to obtain 
corrective actions from a manufacturer or other source, use these 
actions if they are FAA-approved. Corrective actions are considered 
FAA-approved if they are approved by the State of Design Authority 
(or their delegated agent). You are required to assure the product 
is airworthy before it is returned to service.
    (3) Special Flight Permits: Special flight permits may be issued 
in accordance with sections 21.197 and 21.199 of the Federal 
Aviation Regulations (14 CFR 21.197 and 21.199) to operate the 
airplane to a location where the airplane can be inspected (if the 
operator elects to do so), provided that the procedures and 
limitations in paragraphs (v)(3)(i) and (v)(3)(ii) of this AD are 
adhered to.
    (i) Flight Crew Limitations and Procedures:
    (A) Ferry flight with gear extended and pinned;
    (B) Landing to be conducted at a minimum descent rate;
    (C) Minimize braking on landing;
    (D) Only essential crew on board; and
    (E) Flight in known or forecast icing condition is prohibited.
    (ii) Maintenance Procedures:
    (A) Do the general visual inspection required by paragraph (h) 
of this AD;
    (B) Do the general visual inspections of the stabilizer stay and 
the hinge points of the MLG for general condition and security, in 
accordance with Bombardier Q400 All Operator Message 236A, dated 
September 11, 2007;
    (C) If no discrepancy is detected during the inspections 
required by paragraph (v)(3)(ii)(A) and (v)(3)(ii)(B) of this AD, 
before further flight, insert the ground lock pins and a wire lock 
of the MLG in place.
    (D) Ensure the nose landing gear ground lock is engaged.

Related Information

    (w) Refer to MCAI Canadian Airworthiness Directive CF-2007-20R2, 
dated February 6, 2009; Bombardier Service Bulletin 84-32-55, 
Revision A, dated March 10, 2008; Bombardier Service Bulletin 84-32-
60, Revision A, dated September 29, 2008; Bombardier Repair Drawing 
8/4-32-059, Issue 7, dated June 26, 2008; Bombardier TR MRB-35, 
dated November 18, 2008, to the Bombardier Q400 Dash 8 Maintenance 
Requirements Manual (PSM 1-84-7); and

[[Page 56294]]

Bombardier Q400 All Operator Message 236A, dated September 11, 2007; 
for related information.

Material Incorporated by Reference

    (x) You must use the service information contained in Table 2 of 
this AD to do the actions required by this AD, as applicable, unless 
the AD specifies otherwise. If accomplished, you must use Bombardier 
Q400 All Operator Message 236A, dated September 11, 2007, to do the 
actions specified in paragraph (v)(3)(ii)(B) of this AD. The 
document number and date of the Bombardier Q400 all operator message 
are identified only on the first page of that document.

                        Table 2--Material Incorporated by Reference for Required Actions
----------------------------------------------------------------------------------------------------------------
               Document                            Revision/Issue                            Date
----------------------------------------------------------------------------------------------------------------
Bombardier Service Bulletin 84-32-55..  A..................................  March 10, 2008.
Bombardier Service Bulletin 84-32-60..  A..................................  September 29, 2008.
Bombardier Repair Drawing 8/4-32-059..  Issue 7............................  June 26, 2008.
Bombardier Temporary Revision MRB-35    ...................................  November 18, 2008.
 to the Bombardier Q400 Dash 8
 Maintenance Requirements Manual (PSM
 1-84-7).
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     (1) The Director of the Federal Register approved the 
incorporation by reference of this service information under 5 
U.S.C. 552(a) and 1 CFR part 51.
    (2) For service information identified in this AD, contact 
Bombardier, Inc., Q-Series Technical Help Desk, 123 Garratt 
Boulevard, Toronto, Ontario M3K 1Y5, Canada; telephone 416-375-4000; 
fax 416-375-4539; e-mail <a href="/cdn-cgi/l/email-protection#ff8b979bd18e8c9a8d969a8cbf9e9a8d90d19d90929d9e8d9b969a8dd19c9092"><span class="__cf_email__" data-cfemail="b6c2ded298c7c5d3c4dfd3c5f6d7d3c4d998d4d9dbd4d7c4d2dfd3c498d5d9db">[email&#160;protected]</span></a>; Internet 
<a href="http://www.bombardier.com">http://www.bombardier.com</a>. (The document number of Bombardier Repair 
Drawing 8/4-32-059 is identified as 8/4-32-0059 in the technical 
publications database on <a href="http://www.bombardier.com">http://www.bombardier.com</a>.)
    (3) You may review copies of the 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.
    (4) You may also review copies of the service information that 
is incorporated by reference at the National Archives and Records 
Administration (NARA). For information on the availability of this 
material at NARA, call 202-741-6030, or go to: <a href="http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html">http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html</a>.

    Issued in Renton, Washington, on August 11, 2011.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2011-22468 Filed 9-12-11; 8:45 am]
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