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

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REGISTER issue of each week.

Rules and Regulations Federal Register

39787 

Vol. 75, No. 133 

Tuesday, July 13, 2010 

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 workhours 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 


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39788 Federal Register / Vol. 75, No. 133 / Tuesday, July 13, 2010 / Rules and Regulations 

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 

■ Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 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. 

§ 39.13 [Amended] 

■ 2. The FAA amends § 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/ 


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Federal Register / Vol. 75, No. 133 / Tuesday, July 13, 2010 / Rules and Regulations 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 Part 2, Airworthiness Limitation Items, of 

the Bombardier Dash 8 Q400 Maintenance Requirements Manual, PSM 1–84–7.

Original ........................................ August 15, 2008. 

Bombardier Temporary Revision ALI–89 to Part 2, Airworthiness Limitation Items, of 

the Bombardier Dash 8 Q400 Maintenance Requirements Manual, PSM 1–84–7.

Original ........................................ March 27, 2009. 

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.

11 ................................................. August 22, 2008. 

(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 Coˆte-Vertu Road West, Dorval, 

Que ́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; email 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 


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