9756 Federal Register / Vol. 75, No. 42 / Thursday, March 4, 2010 / Rules and Regulations 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0712; Directorate 

Identifier 2007–NM–152–AD; Amendment 

39–16205; AD 2010–04–12] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier, 

Inc. Model DHC–8–100 and DHC–8–200 

Series Airplanes, and Model DHC–8– 

301, –311, and –315 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Model DHC–8–100 and DHC–8–200 

series airplanes, and DHC–8–301, –311, 

and –315 airplanes. This AD requires 

implementing a corrosion prevention 

and control program (CPCP) either by 

accomplishing specific tasks or by 

revising the maintenance inspection 

program to include a CPCP. This AD 

results from the determination that, as 

airplanes age, they are more likely to 

exhibit indications of corrosion. We are 

issuing this AD to prevent structural 

failure of the airplane due to corrosion. 

DATES: This AD is effective April 8, 

2010. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of April 8, 2010. 

ADDRESSES: For 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. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Management Facility between 9 

a.m. and 5 p.m., Monday through 

Friday, except Federal holidays. The AD 

docket contains this AD, the regulatory 

evaluation, any comments received, and 

other information. The address for the 

Docket Office (telephone 800–647–5527) 

is the Document Management Facility, 

U.S. Department of Transportation, 

Docket Operations, M–30, West 

Building Ground Floor, Room W12–140, 

1200 New Jersey Avenue, SE., 

Washington, DC 20590. 

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 airworthiness 

directive (AD) that would apply to 

certain Bombardier Model DHC–8–100 

and DHC–8–200 series airplanes, and 

DHC–8–301, –311, and –315 airplanes. 

That NPRM was published in the 

Federal Register on August 13, 2009 (74 

FR 40778). That NPRM proposed to 

require implementing a corrosion 

prevention and control program (CPCP) 

either by accomplishing specific tasks or 

by revising the maintenance inspection 

program to include a CPCP. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

considered the comment received from 

the single commenter. 

Request for Clarification of Inspections 

Mesa Airlines requests that we restate 

that the inspections required by 

paragraph (h) of this AD to specify to 

inspect for Environmental Damage and/ 

or Corrosion Protection and Control 

Program (ED/CPCP). The commenter 

asserts that the NPRM would require 

only tasks identified as both ED and 

CPCP. Mesa Airlines notes that 

accomplishing the ED/CPCP inspections 

only does not encompass the Air 

Transport Association (ATA) of America 

Codes listed in the NPRM. 

We agree. Canadian AD CF–2007–06, 

dated April 10, 2007, describes doing 

‘‘ED/CPCP’’ inspections. The required 

actions include ‘‘ED’’ inspections and 

inspections identified as both ‘‘ED’’ and 

‘‘CPCP.’’ We have clarified this in 

paragraph (h) of this AD. This has been 

coordinated with TCCA. We have also 

revised paragraphs (i) and (i)(2) of this 

AD to clarify the inspections. 

Explanation of Change Made to This 

AD 

We have revised this AD to identify 

the legal name of the manufacturer as 

published in the most recent type 

certificate data sheet for the affected 

airplane models. 

Conclusion 

We reviewed the relevant data, 

considered the comment received, and 

determined that air safety and the 

public interest require adopting the AD 

with the changes described previously. 

We also determined that these changes 

will not increase the economic burden 

on any operator or increase the scope of 

the AD. 

Explanation of Change to Costs of 

Compliance 

Since issuance of the NPRM, we have 

increased the labor rate used in the 

Costs of Compliance from $80 per workhour to $85 per work-hour. The Costs of 

Compliance information, below, reflects 

this increase in the specified hourly 

labor rate. 

Costs of Compliance 

This AD affects about 154 airplanes of 

U.S. registry. There are between 16 and 

17 specific inspections, depending on 

the applicable manual identified in 

Table 1 of this AD. The inspections take 

about 53 work hours per airplane, per 

inspection cycle, at an average labor rate 

of $85 per work hour. Based on these 

figures, the estimated cost of this AD for 

U.S. operators is $693,770, or $4,505 per 

airplane, per inspection cycle. 

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 

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 that this AD: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 


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Federal Register / Vol. 75, No. 42 / Thursday, March 4, 2010 / Rules and Regulations 9757 

(2) Is not a ‘‘significant rule’’ under 

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. 

You can find our regulatory 

evaluation and the estimated costs of 

compliance in the AD Docket. 

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: 

2010–04–12 Bombardier, Inc.: Amendment 

39–16205. Docket No. FAA–2009–0712; 

Directorate Identifier 2007–NM–152–AD. 

Effective Date 

(a) This airworthiness directive (AD) is 

effective April 8, 2010. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Bombardier, Inc. 

Model DHC–8–101, DHC–8–102, DHC–8– 

103, DHC–8–106, DHC–8–201, DHC–8–202, 

DHC–8–301, DHC–8–311, and DHC–8–315 

airplanes, certificated in any category; serial 

numbers 003 and subsequent. 

Subject 

(d) Air Transport Association (ATA) of 

America Codes 32: Landing Gear, 51: 

Standard Practices/Structures; 52: Doors; 53: 

Fuselage; 54: Nacelles/Pylons; 55: Stabilizers; 

and 57: Wings. 

Unsafe Condition 

(e) This AD results from the determination 

that, as airplanes age, they are more likely to 

exhibit indications of corrosion. We are 

issuing this AD to prevent structural failure 

of the airplane due to corrosion. 

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. 

Manual References 

(g) This AD refers to the manuals listed in 

Table 1 of this AD. 

TABLE 1—APPLICABLE MANUALS

Bombardier model Manual 

(1) DHC–8–101, –102, –103, and –106 airplanes.Part 1, Section 3, Structural Inspection Program, of the Bombardier de Havilland Dash 8 Maintenance Program Maintenance Review Board Report Dash 8 Series 100 Program Support 

Manual (PSM) 1–8–7, Revision 22, dated November 1, 2008. 

(2) DHC–8–201 and DHC–8–202 airplanes ....... Part 1, Section 3, Structural Inspection Program, of the Bombardier de Havilland Dash 8 Maintenance Program Maintenance Review Board Report Dash 8 Series 200 PSM 1–82–7, Revision 13, dated November 1, 2008. 

(3) Model DHC–8–301, DHC–8–311, and DHC– 

8–315 airplanes.

Part 1, Section 3, Structural Inspection Program, of the Bombardier de Havilland Dash 8 Maintenance Program Maintenance Review Board Report Dash 8 Series 300, PSM 1–83–7, Revision 22, dated November 1, 2008. 

Inspections 

(h) At the later of the times specified in 

paragraphs (h)(1) and (h)(2) of this AD, do 

each of the Environmental Damage/Corrosion 

Protection and Control Program (ED/CPCP) 

inspections identified with both ‘‘ED’’ and 

‘‘CPCP,’’ or with only ‘‘ED,’’ including reprotection tasks, as applicable, which are 

found in the ‘‘Type of Damage’’ column of the 

applicable manual found in Table 1 of this 

AD, in accordance with the applicable 

manual identified in Table 1 of this AD. 

Except as provided by paragraph (i) of this 

AD, repeat each task thereafter at intervals 

not to exceed the compliance time specified 

in the ‘‘Repeat’’ column of the applicable 

manual identified in Table 1 of this AD. 

(1) Within 24 months after the effective 

date of this AD. 

(2) At the compliance time specified in the 

‘‘Threshold’’ column of the applicable manual 

identified in Table 1 of this AD since the date 

of issuance of the original Canadian 

airworthiness certificate or the date of 

issuance of the original Canadian export 

certificate of airworthiness. If there is no 

value in the ‘‘Threshold’’ column, use the 

time specified in the ‘‘Repeat’’ column. 

(i) After accomplishment of each initial 

ED/CPCP and ED task required by paragraph 

(h) of this AD, the FAA may approve the 

incorporation into the operator’s approved 

maintenance/inspection program of the CPCP 

specified in the applicable manual identified 

in Table 1 of this AD; or the equivalent 

program that is approved in accordance with 

this AD. In all cases, the initial corrosion task 

for each airplane area must be completed by 

the initial compliance time specified in 

paragraph (h) of this AD. 

(1) Any operator complying with paragraph 

(i) of this AD may use an alternative 

recordkeeping method to that otherwise 

required by section 91.417 (‘‘Maintenance 

records’’) or section 121.380 (‘‘Maintenance 

recording requirements’’) of the Federal 

Aviation Regulations (14 CFR 91.417 or 14 

CFR 121.380, respectively) for the actions 

required by this AD, provided that the 

recordkeeping method is approved by the 

FAA and is included in a revision to the 

maintenance/inspection program. For the 

purposes of this paragraph, ‘‘the FAA’’ is 

defined as the cognizant Principal 

Maintenance Inspector (PMI) for operators 

that are assigned a PMI (i.e., part 121, 125, 

and 135 operators), and the cognizant Flight 

Standards District Office for other operators 

(i.e., part 91 operators). 

(2) After the initial accomplishment of the 

ED/CPCP and ED tasks required by paragraph 

(h) of this AD, any extension of the repetitive 

intervals specified in the manual must be 

approved by the Manager, New York Aircraft 

Certification Office (ACO), FAA. 

Corrective Actions 

(j) If any corrosion is found during 

accomplishment of any action required by 

paragraph (h) of this AD: Before further 

flight, rework, repair, or replace, as 

applicable, in accordance with a method 

approved by either the Manager, New York 

ACO, FAA; or Transport Canada Civil 

Aviation (TCCA) (or its delegated agent). 

Reporting Requirements for Level 3 

Corrosion Findings 

(k) If any Level 3 corrosion, as defined in 

Part 1 of the Bombardier (de Havilland) 

DHC–6 Twin Otter, Dash 7 & Dash 8 

Corrosion Prevention and Control Manual, 

PSM 1–GEN–5, Revision 3, dated November 

30, 1998, is found during the 

accomplishment of any action required by 

this AD, do paragraphs (k)(1), (k)(2), and 

(k)(3) of 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. 

(1) Within 3 days after the finding of Level 

3 corrosion, report findings to the Manager, 

New York ACO, FAA, in accordance with the 

Bombardier (de Havilland) DHC–6 Twin 

Otter, Dash 7 & Dash 8 Corrosion Prevention 

and Control Manual, PSM 1–GEN–5, 

Revision 3, dated November 30, 1998. 


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(2) Within 10 days after the finding of 

Level 3 corrosion, either submit a plan to the 

FAA to identify a schedule for accomplishing 

the applicable CPCP task on the remainder of 

the airplanes in the operator’s fleet that are 

subject to this AD, or provide data 

substantiating that the Level 3 corrosion that 

was found is an isolated case. The FAA may 

impose a schedule other than that proposed 

in the plan upon finding that a change to the 

schedule is needed to ensure that any other 

Level 3 corrosion is detected in a timely 

manner. For the purposes of this paragraph, 

‘‘the FAA’’ is defined as the cognizant 

Principal Maintenance Inspector (PMI) for 

operators that are assigned a PMI (i.e., part 

121, 125, and 135 operators), and the 

cognizant Flight Standards District Office for 

other operators (i.e., part 91 operators). 

(3) Within the time schedule approved in 

accordance with paragraph (k)(2) of this AD, 

accomplish the applicable task on the 

remainder of the airplanes in the operator’s 

fleet that are subject to this AD. 

Limiting Future Corrosion Findings 

(l) If corrosion findings that exceed Level 

1 are found in any area during any repeat of 

any CPCP task after the initial 

accomplishment required by paragraph (h) of 

this AD: Within 60 days after such finding, 

implement a means approved by the FAA to 

reduce future findings of corrosion in that 

area to Level 1 or better. For the purposes of 

this paragraph, ‘‘the FAA’’ is defined as the 

cognizant PMI for operators that are assigned 

a PMI (i.e., part 121, 125, and 135 operators), 

and the cognizant Flight Standards District 

Office for other operators (i.e., part 91 

operators). 

Scheduling Corrosion Tasks for Transferred 

Airplanes 

(m) Before any airplane subject to this AD 

is transferred and placed into service by an 

operator: Establish a schedule for 

accomplishing the CPCP tasks required by 

this AD in accordance with paragraph (m)(1) 

or (m)(2) of this AD, as applicable. 

(1) For airplanes on which the CPCP tasks 

required by this AD have been accomplished 

previously at the schedule established by this 

AD: Perform the first CPCP task in each area 

in accordance with the previous operator’s 

schedule, or in accordance with the new 

operator’s schedule, whichever results in an 

earlier accomplishment of that CPCP task. 

After the initial accomplishment of each 

CPCP task in each area as required by this 

paragraph, repeat each CPCP task in 

accordance with the new operator’s schedule. 

(2) For airplanes on which the CPCP tasks 

required by this AD have not been 

accomplished previously, or have not been 

accomplished at the schedule established by 

this AD: The new operator must perform 

each initial CPCP task in each area before 

further flight or in accordance with a 

schedule approved by the FAA. For the 

purposes of this paragraph, ‘‘the FAA’’ is 

defined as the cognizant Principal 

Maintenance Inspector (PMI) for operators 

that are assigned a PMI (i.e., part 121, 125, 

and 135 operators), and the cognizant Flight 

Standards District Office for other operators 

(i.e., part 91 operators). 

Alternative Methods of Compliance 

(AMOCs) 

(n)(1) The Manager, New York 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. 

(2) To request a different method of 

compliance or a different compliance time 

for this AD, follow the procedures in 14 CFR 

39.19. Before using any approved AMOC on 

any airplane to which the AMOC applies, 

notify your principal maintenance inspector 

(PMI) or principal avionics inspector (PAI), 

as appropriate, or lacking a principal 

inspector, your local Flight Standards District 

Office. The AMOC approval letter must 

specifically reference this AD. 

Related Information 

(o) Canadian airworthiness directive CF– 

2007–06, dated April 10, 2007, also addresses 

the subject of this AD. 

Material Incorporated by Reference 

(p) You must use the service information 

contained in Table 2 of this AD, as 

applicable, to do the actions required by this 

AD, unless the AD specifies otherwise. 

TABLE 2—MATERIAL INCORPORATED BY REFERENCE

Document Revision Date 

Part 1, Section 3, Structural Inspection Program, of the Bombardier de Havilland Dash 8 Maintenance Program Maintenance Review Board Report Dash 8 Series 100 Program Support Manual (PSM) 1–8–7.22 November 1, 2008. 

Part 1, Section 3, Structural Inspection Program, of the Bombardier de Havilland Dash 8 Maintenance Program Maintenance Review Board Report Series 200 PSM 1–82–7.13 November 1, 2008. 

Part 1, Section 3, Structural Inspection Program, of the Bombardier de Havilland Dash 8 Maintenance Program Maintenance Review Board Report Dash 8 Series 300, PSM 1–83–7.22 November 1, 2008. 

Bombardier (de Havilland) DHC–6 Twin Otter, Dash 7 & Dash 8 Corrosion Prevention and Control Manual, 

PSM 1-GEN–5, Part 1.

3 November 30, 1998. 

Bombardier de Havilland Dash 8 

Maintenance Program Maintenance Review 

Board Report Dash 8 Series 100 PSM 1–8–7, 

Revision 22, dated November 1, 2008, 

contains the following effective pages: 

LIST OF EFFECTIVE PAGES

Page title/ 

description Page number(s) Revision number Date shown on page(s) 

Title Page .............................................................................. None shown .......................... 22 .......................................... November 1, 2008. 

List of Effective Pages .......................................................... 1–4 ........................................ None shown* ........................ November 1, 2008. 

Log of Revisions ................................................................... 1–18 ...................................... None shown* ........................ November 1, 2008. 

Record of Revisions .............................................................. 1–2 ........................................ 22 .......................................... November 1, 2008. 

Contents ................................................................................ 1–4 ........................................ None shown* ........................ November 1, 2008. 

Section 3: 

Subject 3–0 .................................................................... 1–4 ........................................ None shown* ........................ November 1, 2008. 

Subject 3–32 .................................................................. 1–2 ........................................ None shown* ........................ November 1, 2008. 

Subject 3–52 .................................................................. 1–2 ........................................ None shown* ........................ November 1, 2008. 

Subject 3–53 .................................................................. 1–16 ...................................... None shown* ........................ November 1, 2008. 

Subject 3–54 .................................................................. 1–4 ........................................ None shown* ........................ November 1, 2008. 

Subject 3–55 .................................................................. 1–8 ........................................ None shown* ........................ November 1, 2008. 

Subject 3–57 .................................................................. 1–12 ...................................... None shown* ........................ November 1, 2008. 


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Bombardier de Havilland Dash 8 

Maintenance Program Maintenance Review 

Board Report Dash 8 Series 200 PSM 1–82– 

7, Revision 13, dated November 1, 2008, 

contains the following effective pages: 

LIST OF EFFECTIVE PAGES

Page title/ 

description Page number(s) Revision number Date shown on page(s) 

Title Page .............................................................................. None shown .......................... 13 .......................................... November 1, 2008. 

List of Effective Pages .......................................................... 1–4 ........................................ None shown* ........................ November 1, 2008. 

Log of Revisions ................................................................... 1–8 ........................................ None shown* ........................ November 1, 2008. 

Record of Revisions .............................................................. 1–2 ........................................ 13 .......................................... November 1, 2008. 

Contents ................................................................................ 1–4 ........................................ None shown* ........................ November 1, 2008. 

Section 3: 

Subject 3–0 .................................................................... 1–4 ........................................ None shown* ........................ November 1, 2008. 

Subject 3–32 .................................................................. 1–2 ........................................ None shown* ........................ November 1, 2008. 

Subject 3–52 .................................................................. 1–2 ........................................ None shown* ........................ November 1, 2008. 

Subject 3–53 .................................................................. 1–16 ...................................... None shown* ........................ November 1, 2008. 

Subject 3–54 .................................................................. 1–4 ........................................ None shown* ........................ November 1, 2008. 

Subject 3–55 .................................................................. 1–6 ........................................ None shown* ........................ November 1, 2008. 

Subject 3–57 .................................................................. 1–12 ...................................... None shown* ........................ November 1, 2008. 

Bombardier de Havilland Dash 8 

Maintenance Program Maintenance Review 

Board Report Dash 8 Series 300 PSM 1–83– 

7, Revision 22, dated November 1, 2008, 

contains the following effective pages: 

LIST OF EFFECTIVE PAGES

Page title/description Page number(s) Revision number Date shown 

on page(s) 

Title Page .............................................................................. None shown .......................... 22 .......................................... November 1, 2008. 

List of Effective Pages .......................................................... 1–4 ........................................ None shown* ........................ November 1, 2008. 

Log of Revisions ................................................................... 1–18 ...................................... None shown* ........................ November 1, 2008. 

Record of Revisions .............................................................. 1–2 ........................................ 22 .......................................... November 1, 2008. 

Contents ................................................................................ 1–4 ........................................ None shown* ........................ November 1, 2008. 

Section 3: 

Subject 3–0 .................................................................... 1–4 ........................................ None shown* ........................ November 1, 2008. 

Subject 3–32 .................................................................. 1–2 ........................................ None shown* ........................ November 1, 2008. 

Subject 3–52 .................................................................. 1–2 ........................................ None shown* ........................ November 1, 2008. 

Subject 3–53 .................................................................. 1–18 ...................................... None shown* ........................ November 1, 2008. 

Subject 3–54 .................................................................. 1–4 ........................................ None shown* ........................ November 1, 2008. 

Subject 3–55 .................................................................. 1–8 ........................................ None shown* ........................ November 1, 2008. 

Subject 3–57 .................................................................. 1–12 ...................................... None shown* ........................ November 1, 2008. 

(*Only the title page and Record of Revisions of these documents specify the revision level of these documents.) 

Bombardier (de Havilland) DHC–6 Twin 

Otter, Dash 7 & Dash 8 Corrosion Prevention 

and Control Manual PSM 1–GEN–5, Part 1, 

Revision 3, dated November 30, 1998, 

contains the following effective pages: 

LIST OF EFFECTIVE PAGES

Page title/ 

description Page number(s) Revision number Date shown on page(s) 

Title Page ............................................................................. None shown .......................... None shown* ........................ November 8, 1993. 

Record of Revisions ............................................................. 1 ............................................ 3 ............................................ August 27, 1991. 

............................................................................................... 2 ............................................ None shown* ........................ August 27, 1991. 

Part 1 List of Effective Pages ............................................... 1–2 ........................................ None shown* ........................ November 30, 1998. 

Part 1 Table of Contents ...................................................... 1–4 ........................................ None shown* ........................ November 8, 1993. 

Part 1 List of Illustrations ...................................................... 1–2 ........................................ None shown* ........................ November 8, 1993. 

Part 1 List of Tables ............................................................. 1 ............................................ None shown* ........................ November 8, 1993. 

2 ............................................ None shown* ........................ August 27, 1991. 

Introduction ........................................................................... 1–2 ........................................ None shown* ........................ November 8, 1993. 

3–4 ........................................ None shown* ........................ November 5, 1992. 

Chapter 1 .............................................................................. 1–1 through 1–10 ................. None shown* ........................ November 8, 1993. 

Chapter 2 .............................................................................. 2–1 through 2–6 ................... None shown* ........................ November 8, 1993. 

Chapter 3 .............................................................................. 3–1 through 3–4 ................... None shown* ........................ November 8, 1993. 

Chapter 4 .............................................................................. 4–1 through 4–44 ................. None shown* ........................ November 8, 1993. 

Chapter 5 .............................................................................. 5–1 through 5–48 ................. None shown* ........................ November 8, 1993. 

Chapter 6 .............................................................................. 6–1 through 6–8, ..................

6–11 through 6–16 ...............

None shown* ........................ August 27, 1991. 


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LIST OF EFFECTIVE PAGES—Continued 

Page title/ 

description Page number(s) Revision number Date shown on page(s) 

6–9 ........................................ None shown* ........................ November 8, 1993. 

6–10 ...................................... None shown* ........................ November 5, 1992. 

Chapter 7 .............................................................................. 7–1 through 7–2 ................... None shown* ........................ November 8, 1993. 

Chapter 8 .............................................................................. 8–1 through 8–4 ................... None shown* ........................ November 8, 1993. 

Chapter 9 .............................................................................. 9–1 through 9–4 ................... None shown* ........................ November 30, 1998. 

(*Only page 1 of the Record of Revisions of Bombardier (de Havilland) DHC–6 Twin Otter, Dash 7 & Dash 8 Corrosion Prevention and Control 

Manual PSM 1–GEN– 5, Part 1, Revision 3, contains the revision level of this document.) 

(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., 400 CoˆteVertu 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) 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 or 425–227–1152. 

(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: http://www.archives.gov/federal_register/ 

code_of_federal_regulations/ 

ibr_locations.html. 

Issued in Renton, Washington, on February 

11, 2010. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–3226 Filed 3–3–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0718; Directorate 

Identifier 2009–NM–025–AD; Amendment 

39–16212; AD 2010–05–03] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Model 747–100, 747–100B, 

747–100B SUD, 747–200B, 747–200C, 

747–200F, 747–300, 747–400, 747– 

400D, 747–400F, 747SR, and 747SP 

Series Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all 

Model 747–100, 747–100B, 747–100B 

SUD, 747–200B, 747–200C, 747–200F, 

747–300, 747–400, 747–400D, 747– 

400F, 747SR, and 747SP series 

airplanes. This AD requires one-time 

detailed and high frequency eddy 

current inspections for cracks in the 

wing and horizontal stabilizer side-ofbody joints and the fuselage skin 

circumferential splices, and repair if 

necessary. This AD also requires, for 

certain airplanes, repetitive detailed 

inspections for cracks of the fuselage 

skin circumferential splices, and repair 

if necessary. This AD results from 

Boeing analysis indicating that the wing 

and horizontal stabilizer side-of-body 

joints, and the fuselage skin 

circumferential splices, are susceptible 

to fatigue cracking due to high cyclic 

loads on the airplane. We are issuing 

this AD to detect and correct fatigue 

cracking at multiple adjacent locations 

in the subject areas, which could 

connect to form large cracks and result 

in reduced structural integrity leading to 

rapid decompression and consequent 

loss of control of the airplane. 

DATES: This AD is effective April 8, 

2010. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of April 8, 2010. 

ADDRESSES: For service information 

identified in this AD, contact Boeing 

Commercial Airplanes, Attention: Data 

& Services Management, P.O. Box 3707, 

MC 2H–65, Seattle, Washington 98124– 

2207; telephone 206–544–5000, 

extension 1; fax 206–766–5680; e-mail 

me.boecom@boeing.com; Internet 

https://www.myboeingfleet.com. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Management Facility between 9 

a.m. and 5 p.m., Monday through 

Friday, except Federal holidays. The AD 

docket contains this AD, the regulatory 

evaluation, any comments received, and 

other information. The address for the 

Docket Office (telephone 800–647–5527) 

is the Document Management Facility, 

U.S. Department of Transportation, 

Docket Operations, M–30, West 

Building Ground Floor, Room W12–140, 

1200 New Jersey Avenue, SE., 

Washington, DC 20590. 

FOR FURTHER INFORMATION CONTACT: Ivan 

Li, Aerospace Engineer, Airframe 

Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office, 1601 Lind 

Avenue, SW., Renton, Washington 

98057–3356; telephone (425) 917–6437; 

fax (425) 917–6590. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an airworthiness 

directive (AD) that would apply to all 

Model 747 airplanes. That NPRM was 

published in the Federal Register on 

August 25, 2009 (74 FR 42807). That 

NPRM proposed to require one-time 

detailed and high frequency eddy 

current inspections for cracks in the 

wing and horizontal stabilizer side-ofbody joints and the fuselage skin 

circumferential splices, and repair if 

necessary. That NPRM also proposed to 

require, for certain airplanes, repetitive 

detailed inspections for cracks of the 

fuselage skin circumferential splices, 

and repair if necessary. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

considered the comments received. 

Supportive Comment 

Boeing concurs with the contents of 

the NPRM. 

Requests To Change Compliance Times 

UPS asks that we change the NPRM 

to extend the compliance time for the 

inspections specified in Table 3 of 

paragraph 1.E. of Boeing Alert Service 

Bulletin 747–51A2060, dated October 

30, 2008, and required by paragraph (g) 

of the NPRM. UPS states that the 

inspections are not to be done until at 

least 28,500 total flight cycles or 

130,000 total flight hours, whichever 

occurs later, have been accumulated on 


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