```

[Federal Register: July 13, 2010 (Volume 75, Number 133)]
[Rules and Regulations]               
[Page 39787-39789]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr13jy10-1]                         

========================================================================
Rules and Regulations
                                                Federal Register
________________________________________________________________________

This section of the FEDERAL REGISTER contains regulatory documents 
having general applicability and legal effect, most of which are keyed 
to and codified in the Code of Federal Regulations, which is published 
under 50 titles pursuant to 44 U.S.C. 1510.

The Code of Federal Regulations is sold by the Superintendent of Documents. 
Prices of new books are listed in the first FEDERAL REGISTER issue of each 
week.

========================================================================

[[Page 39787]]

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2010-0229; Directorate Identifier 2009-NM-115-AD; 
Amendment 39-16356; AD 2010-14-11]
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.

-----------------------------------------------------------------------

SUMMARY: We are adopting a new airworthiness directive (AD) for 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:

    Certain main landing gear components have experienced premature 
failure during certification testing. Revision has been made to the 
DHC-8-400 Maintenance Requirements Manual, Airworthiness Limitation 
Items, to incorporate the revised safe life limits for the main 
landing gear lock actuator assembly, retraction actuator assembly 
rod end and piston, and the upper bearing in the main landing gear 
shock strut assembly. Failure of these components could adversely 
affect the structural integrity of the main landing gear.

* * * * *
We are issuing this AD to require actions to correct the unsafe 
condition on these products.

DATES: This AD becomes effective August 17, 2010.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of August 17, 
2010.

ADDRESSES: You may examine the AD docket on the Internet at http://www.regulations.gov 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, 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 17, 2010 (75 
FR 12710). That NPRM proposed to correct an unsafe condition for the 
specified products. The MCAI states:

    Certain main landing gear components have experienced premature 
failure during certification testing. Revision has been made to the 
DHC-8-400 Maintenance Requirements Manual, Airworthiness Limitation 
Items, to incorporate the revised safe life limits for the main 
landing gear lock actuator assembly, retraction actuator assembly 
rod end and piston, and the upper bearing in the main landing gear 
shock strut assembly. Failure of these components could adversely 
affect the structural integrity of the main landing gear.
    This [Canadian airworthiness] directive is issued to ensure safe 
operation of the main landing gear during its service life.

The corrective actions include revising the Airworthiness Limitations 
section of the Instructions for Continued Airworthiness, replacing the 
upper bearing on certain airplanes, and replacing certain rod ends. 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 or on the determination of 
the cost to the public.

Conclusion

    We reviewed the available data and determined that air safety and 
the public interest require adopting the AD as proposed.

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

Costs of Compliance

    We estimate that this AD will affect 62 products of U.S. registry. 
We also estimate that it will take about 22 work-hours per product to 
comply with the basic requirements of this AD. The average labor rate 
is $85 per work-hour. Required parts will cost about $18,588 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 $1,268,396, or $20,458 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

[[Page 39788]]

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 http://www.regulations.gov; 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, 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

0
Accordingly, under the authority delegated to me by the Administrator, 
the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

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

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

Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by adding the following new AD:

2010-14-11 Bombardier, Inc.: Amendment 39-16356. Docket No. FAA-
2010-0229; Directorate Identifier 2009-NM-115-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective August 
17, 2010.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Bombardier, Inc. Model DHC-8-400, -401, 
and -402 airplanes, having serial numbers (S/Ns) 4001, 4003, 4004, 
4006, and 4008 through 4227 inclusive, certificated in any category.

    Note 1:  This AD requires revisions to certain operator 
maintenance documents to include new inspections. Compliance with 
these inspections is required by 14 CFR 91.403(c). For airplanes 
that have been previously modified, altered, or repaired in the 
areas addressed by these inspections, the operator may not be able 
to accomplish the inspections described in the revisions. In this 
situation, to comply with 14 CFR 91.403(c), the operator must 
request approval for an alternative method of compliance according 
to paragraph (j)(1) of this AD. The request should include a 
description of changes to the required inspections that will ensure 
the continued damage tolerance of the affected structure. The FAA 
has provided guidance for this determination in Advisory Circular 
(AC) 25.1529-1A.

Subject

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

Reason

    (e) The mandatory continuing airworthiness information (MCAI) 
states:
    Certain main landing gear components have experienced premature 
failure during certification testing. Revision has been made to the 
DHC-8-400 Maintenance Requirements Manual, Airworthiness Limitation 
Items (ALI), to incorporate the revised safe life limits for the 
main landing gear lock actuator assembly, retraction actuator 
assembly rod end and piston, and the upper bearing in the main 
landing gear shock strut assembly. Failure of these components could 
adversely affect the structural integrity of the main landing gear.
    This [Canadian airworthiness] directive is issued to ensure safe 
operation of the main landing gear during its service life.

The corrective actions include revising the Airworthiness 
Limitations section (ALS) of the Instructions for Continued 
Airworthiness, replacing the upper bearing on certain airplanes, and 
replacing certain rod ends.

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.

Actions

    (g) For Model DHC-8-400, -401, and -402 airplanes having S/Ns 
4001, 4003, 4004, 4006, and 4008 through 4210 inclusive: Do the 
actions specified in paragraphs (g)(1) and (g)(2) of this AD.
    (1) Within 60 days after the effective date of this AD: Revise 
the ALS of the Instructions for Continued Airworthiness by 
incorporating the revised structural safe life limit for the upper 
bearing having part number (P/N) 46114-1, as provided in Bombardier 
Temporary Revision (TR), ALI-82, dated August 15, 2008, to Part 2, 
Airworthiness Limitation Items, of the Bombardier Dash 8 Q400 
Maintenance Requirements Manual (MRM), PSM 1-84-7. The initial 
compliance time for replacing the upper bearing is specified in 
paragraph (g)(2) of this AD.
    (2) Replace the upper bearing having P/N 46114-1 with a new or 
serviceable upper bearing, in accordance with Goodrich Dressed Shock 
Strut Assembly Main Landing Gear Part No. 46100-29/-31/-33/-35/-37/-
39/-41/-43/-45/-47/-49/-51/-53 and -55 Component Maintenance Manual 
with Illustrated Parts List 32-11-03, Revision 11, dated August 22, 
2008, at the applicable time specified in paragraphs (g)(2)(i), 
(g)(2)(ii), and (g)(2)(iii), of this AD.
    (i) For airplanes having accumulated fewer than 15,000 total 
flight cycles as of the effective date of this AD: Replace prior to 
the accumulation of 15,000 total flight cycles.
    (ii) For airplanes having accumulated 15,000 total flight cycles 
or more, but fewer than 20,000 total flight cycles, as of the 
effective date of this AD: Replace prior to the accumulation of 
20,000 total flight cycles.
    (iii) For airplanes having accumulated 20,000 total flight 
cycles or more as of the effective date of this AD: Replace before 
further flight.
    (h) For Model DHC-8-400, -401, and -402 series airplanes having 
S/Ns 4001, 4003, 4004, 4006, and 4008 through 4227 inclusive: Do the 
applicable actions specified in paragraphs (h)(1) and (h)(2) of this 
AD.
    (1) Within 60 days after the effective date of this AD: Revise 
the ALS of the Instructions for Continued Airworthiness to 
incorporate the revised safe life limits for the retraction actuator 
assembly rod end having P/N P3A2750 and P3A2750-1; retraction 
actuator assembly piston having P/N 46570-5; lock actuator cylinder 
assembly having P/N 46601-1/-3; and lock actuator assembly having P/
N 46600-1/-3/-5/-7; as provided in Bombardier TR ALI-89, dated March 
27, 2009, to Part 2, Airworthiness Limitation Items, of the 
Bombardier Dash 8 Q400 MRM, PSM 1-84-7. The initial compliance time 
for the replacement is specified in the TR, except as provided by 
paragraph (h)(2) of this AD.
    (2) For airplanes with a main landing gear retraction actuator 
assembly rod end that has accumulated more than 9,850 total flight 
cycles as of the effective date of this AD: Within 600 flight cycles 
after the effective date of this AD, replace any affected rod end 
having P/Ns P3A2750 and P3A2750-1 with a new or serviceable rod end, 
in accordance with Goodrich Dressed Shock Strut Assembly Main 
Landing Gear Part No. 46100-29/-31/-33/-35/-37/-39/-41/-43/-45/-47/-
49/-51/

[[Page 39789]]

-53 and -55 Component Maintenance Manual with Illustrated Parts List 
32-11-03, Revision 11, dated August 22, 2008.
    (i) After accomplishing the revision specified in paragraph 
(g)(1) or (h)(1) of this AD, except as provided in paragraph (j) of 
this AD, no alternative replacement times may be approved for this 
part.

    Note 2:  The ALI revisions required by paragraphs (g) and (h) of 
this AD may be done by inserting copies of Bombardier TRs ALI-82 and 
ALI-89 into Part 2, Airworthiness Limitation Items, of the 
Bombardier Dash 8 Q400 MRM, PSM 1-84-7. When these TRs have been 
included in the general revision of the MRM, the general revision 
may be inserted into the MRM, provided the relevant information in 
the general revision is identical to that in Bombardier TRs ALI-82 
and ALI-89.

FAA AD Differences

    Note 3:  This AD differs from the MCAI and/or service 
information as follows: The MCAI and service information do not 
contain replacement procedures for the upper bearings and rod ends. 
This AD requires replacing the upper bearings and rod ends in 
accordance with Goodrich Dressed Shock Strut Assembly Main Landing 
Gear Part No. 46100-29/-31/-33/-35/-37/-39/-41/-43/-45/-47/-49/-51/-
53 and -55 Component Maintenance Manual with Illustrated Parts List 
32-11-03, Revision 11, dated August 22, 2008.

Other FAA AD Provisions

    (j) 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. Send information 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 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.
    (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) Reporting Requirements: For any reporting requirement in 
this AD, under the provisions of the Paperwork Reduction Act (44 
U.S.C. 3501 et seq.), the Office of Management and Budget (OMB) has 
approved the information collection requirements and has assigned 
OMB Control Number 2120-0056.
    (4) Special Flight Permits: Special flight permits, as described 
in Section 21.197 and Section 21.199 of the Federal Aviation 
Regulations (14 CFR 21.197 and 21.199), are allowed, provided that 
the actions required in paragraph (h) of this AD have been 
accomplished.

Related Information

    (k) Refer to MCAI Canadian Airworthiness Directive CF-2009-17, 
dated April 22, 2009; Bombardier TR ALI-82, dated August 15, 2008, 
and Bombardier TR ALI-89, dated March 27, 2009, to Part 2, 
Airworthiness Limitation Items, of the Bombardier Dash 8 Q400 
Maintenance Requirements Manual, PSM 1-84-7; and Goodrich Dressed 
Shock Strut Assembly Main Landing Gear Part No. 46100-29/-31/-33/-
35/-37/-39/-41/-43/- 45/-47/-49/-51/-53 and -55 Component 
Maintenance Manual with Illustrated Parts List 32-11-03, Revision 
11, dated August 22, 2008; for related information.

Material Incorporated by Reference

    (l) You must use the service information listed in Table 1 of 
this AD, as applicable, to do the actions required by this AD, 
unless the AD specifies otherwise.

                                   Table 1--Material Incorporated by Reference
----------------------------------------------------------------------------------------------------------------
           Service information                       Revision                              Date
----------------------------------------------------------------------------------------------------------------
Bombardier Temporary Revision ALI-82 to    Original....................  August 15, 2008.
 Part 2, Airworthiness Limitation Items,
 of the Bombardier Dash 8 Q400
 Maintenance Requirements Manual, PSM 1-
 84-7.
Bombardier Temporary Revision ALI-89 to    Original....................  March 27, 2009.
 Part 2, Airworthiness Limitation Items,
 of the Bombardier Dash 8 Q400
 Maintenance Requirements Manual, PSM 1-
 84-7.
Goodrich Dressed Shock Strut Assembly      11..........................  August 22, 2008.
 Main Landing Gear Part No. 46100-29/-31/-
 33/-35/-37/-39/-41/-43/-45/-47/-49/-51/-
 53 and -55 Component Maintenance Manual
 with Illustrated Parts List 32-11-03.
----------------------------------------------------------------------------------------------------------------

    (The revision level of Goodrich Dressed Shock Strut Assembly 
Main Landing Gear Part No. 46100-29/-31/-33/-35/-37/-39/- 41/-43/-
45/-47/-49/-51/-53 and -55 Component Maintenance Manual with 
Illustrated Parts List 32-11-03, Revision 11, dated August 22, 2008, 
is indicated only on the Record of Revisions; no other page of this 
document contains this information. Page LEP-3/4 is missing from the 
List of Effective Pages of this document; page LEP 3/4 is dated 
August 22, 2008.)
    (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 Bombardier service information identified in this AD, 
contact Bombardier, Inc., 400 C[ocirc]te-Vertu Road West, Dorval, 
Qu[eacute]bec H4S 1Y9, Canada; telephone 514-855-5000; fax 514-855-
7401; e-mail thd.qseries@aero.bombardier.com; Internet http://www.bombardier.com.
    (3) For Goodrich service information identified in this AD, 
contact Goodrich Corporation, Landing Gear, 1400 South Service Road, 
West Oakville L6L 5Y7, Ontario, Canada; telephone 905-825-1568; e-
mail jean.breed@goodrich.com; Internet http://www.goodrich.com/TechPubs.
    (4) 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.
    (5) 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: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.

    Issued in Renton, Washington, on June 23, 2010.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2010-15923 Filed 7-12-10; 8:45 am]
BILLING CODE 4910-13-P
```