12158 Federal Register / Vol. 77, No. 40 / Wednesday, February 29, 2012 / Rules and Regulations 

PART 123—DISASTER LOAN 

PROGRAM 

■ 1. The authority citation for part 123 

is revised to read as follows: 

Authority: 15 U.S.C. 632, 634(b)(6), 636(b), 

636(d), 657n; Pub. L. 102–395, 106 Stat. 

1828, 1864; Pub. L. 103–75, 107 Stat. 739; 

and Pub. L. 106–50, 113 Stat. 245. 

■ 2. Amend § 123.203(a) by revising the 

fourth sentence of paragraph (a) to read 

as follows: 

§ 123.203 What interest rate will my 

business pay on a physical disaster 

business loan and what are the repayment 

terms? 

(a) * * * The maturity of your loan 

depends upon your repayment ability, 

but cannot exceed seven years if you 

have credit elsewhere. * * * 

* * * * * 

Dated: February 17, 2012. 

Karen G. Mills, 

Administrator. 

[FR Doc. 2012–4760 Filed 2–28–12; 8:45 am] 

BILLING CODE 8025–01–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0994; Directorate 

Identifier 2010–NM–143–AD; Amendment 

39–16949; AD 2012–03–08] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier, 

Inc. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are superseding an 

existing airworthiness directive (AD) for 

certain Bombardier, Inc. Model CL–600– 

2C10 (Regional Jet Series 700, 701, & 

702), CL–600–2D15 (Regional Jet Series 

705), and CL–600–2D24 (Regional Jet 

Series 900) airplanes. That AD currently 

requires repetitive detailed inspections 

for cracking or deformation, or pulled or 

missing fasteners, on the lower panel of 

the left- and right-hand main landing 

gear (MLG) doors, as applicable, and 

corrective actions if necessary. That AD 

also reduces the repetitive inspection 

interval for certain airplanes. This new 

AD adds a new modification of the MLG 

door configuration, and removes certain 

airplanes from the applicability. This 

AD was prompted by further analysis of 

the MLG door by the manufacturer. We 

are issuing this AD to prevent failure of 

the lower panel of the MLG door, 

departure of the lower panel from the 

airplane, and consequent damage to 

airplane structure, which could 

adversely affect the airplane’s continued 

safe flight and landing. 

DATES: This AD is effective April 4, 

2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of April 4, 2012. 

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; email 

thd.crj@aero.bombardier.com; Internet 

http://www.bombardier.com. You may 

review copies of the referenced 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. 

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 (phone: 800–647–5527) is 

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: Aziz 

Ahmed, 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; phone: 516–228–7329; fax: (516) 

794–5531; email: aziz.ahmed@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2006–14–05, 

Amendment 39–14676 (71 FR 38979, 

July 11, 2006). That AD applies to the 

specified products. The NPRM was 

published in the Federal Register on 

October 5, 2011 (76 FR 61633). That 

NPRM proposed to continue to require 

repetitive detailed inspections for 

cracking or deformation, or pulled or 

missing fasteners, on the lower panel of 

the left- and right-hand main landing 

gear (MLG) doors, as applicable, and 

corrective actions if necessary. That 

NPRM also proposed to reduce the 

repetitive inspection interval for certain 

airplanes. In addition, that NPRM 

proposed to add a new modification of 

the MLG door configuration, and 

remove certain airplanes from the 

applicability. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

have considered the comment received. 

The Air Line Pilots Association 

International supports the NPRM (76 FR 

61633, October 5, 2011). 

Explanation of Changes Made to This 

AD 

We have revised certain headers 

throughout this AD. We have also 

revised the wording in paragraphs (q) 

and (s) of this AD; this change has not 

changed the intent of these paragraphs. 

Conclusion 

We reviewed the available data, 

including the comment received, and 

determined that air safety and the 

public interest require adopting the AD 

with the changes described previously— 

and minor editorial changes. We have 

determined that these minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM (76 FR 

61633, October 5, 2011) for correcting 

the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (76 FR 61633, 

October 5, 2011). 

Costs of Compliance 

We estimate that this AD affects about 

220 products of U.S. registry. 

The actions that are required by AD 

2006–14–05, Amendment 39–14676 (71 

FR 38979, July 11, 2006), and retained 

in this AD take about 3 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 $255 per product. 

We estimate that it will take about 115 

work-hours per product to comply with 

the new basic requirements of this AD. 

The average labor rate is $85 per workhour. Required parts will cost about 

$0 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 costs. 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 the 

AD on U.S. operators to be $2,150,500, 

or $9,775 per product. 


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Federal Register / Vol. 77, No. 40 / Wednesday, February 29, 2012 / Rules and Regulations 12159 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

Section 106, describes the authority of 

the FAA Administrator. Subtitle VII, 

Aviation Programs, describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in Subtitle VII, 

Part A, Subpart III, Section 44701, 

‘‘General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We have determined that this 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, 

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

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979), 

(3) Will not affect intrastate aviation 

in Alaska, and 

(4) 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. 

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 

removing airworthiness directive (AD) 

2006–14–05, Amendment 39–14676 (71 

FR 38979, July 11, 2006), and adding the 

following new AD: 

2012–03–08 Bombardier Inc.: Amendment 

39–16949; Docket No. FAA–2011–0994; 

Directorate Identifier 2010–NM–143–AD. 

(a) Effective Date 

This airworthiness directive (AD) is 

effective April 4, 2012. 

(b) Affected ADs 

This AD supersedes AD 2006–14–05, 

Amendment 39–14676 (71 FR 38979, July 11, 

2006). 

(c) Applicability 

This AD applies to Bombardier, Inc. Model 

CL–600–2C10 (Regional Jet Series 700, 701, 

& 702) airplanes having serial numbers (S/ 

Ns) 10003 through 10230 inclusive; and 

Model CL–600–2D15 (Regional Jet Series 

705) airplanes; and Model CL–600–2D24 

(Regional Jet Series 900) airplanes having S/ 

Ns 15001 through 15053 inclusive, 15055, 

and 15056; certificated in any category. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 32: Landing gear. 

(e) Reason 

This AD was prompted by further analysis 

of the main landing gear (MLG) door by the 

manufacturer. We are issuing this AD to 

prevent failure of the lower panel of the MLG 

door, departure of the lower panel from the 

airplane, and consequent damage to airplane 

structure, which could adversely affect the 

airplane’s continued safe flight and landing. 

(f) Compliance 

You are responsible for having the actions 

required by this AD performed within the 

compliance times specified, unless the 

actions have already been done. 

(g) Restatement of Requirements of AD 2003– 

19–51, Amendment 39–13353 (68 FR 61615, 

October 29, 2003), With Revised Serial 

Numbers and Service Information: Initial 

Compliance Time 

For Model CL–600–2C10 (Regional Jet 

series 700 & 701) series airplanes, S/Ns 10003 

through 10230 inclusive; and Model CL–600– 

2D24 (Regional Jet series 900) series 

airplanes, S/Ns 15002 through 15053 

inclusive, 15055, and 15056: Perform the 

initial inspection specified in paragraph (h) 

of this AD at the applicable time specified in 

paragraph (g)(1) or (g)(2) of this AD. 

(1) For airplanes with fewer than 1,500 

total flight cycles as of November 3, 2003 (the 

effective date of AD 2003–19–51, 

Amendment 39–13353 (68 FR 61615, October 

29, 2003)): Do the inspections before the 

accumulation of 1,050 total flight cycles, or 

within 50 flight cycles after August 15, 2006 

(the effective date of AD 2006–14–05, 

Amendment 39–14676 (71 FR 38979, July 11, 

2006)), whichever is later. 

(2) For airplanes with 1,500 or more total 

flight cycles as of November 3, 2003: Do the 

inspections within 10 flight cycles after 

August 15, 2006. 

(h) Restatement of Requirements of AD 

2003–19–51, Amendment 39–13353 (68 FR 

61615, October 29, 2003), With Revised 

Serial Numbers and Service Information: 

Inspections 

For Model CL–600–2C10 (Regional Jet 

series 700 & 701) series airplanes, S/Ns 10003 

through 10230 inclusive; and Model CL–600– 

2D24 (Regional Jet series 900) series 

airplanes, S/Ns 15002 through 15053 

inclusive, 15055 and 15056: At the 

applicable time specified in paragraph (g) of 

this AD, perform detailed inspections of the 

lower panel, part number (P/N) CC670– 

10520, of the left- and right-hand MLG doors 

for the conditions and in the areas specified 

in paragraphs (h)(1), (h)(2), (h)(3), and (h)(4) 

of this AD; and Figures 1, 2, and 3 of this AD. 

For the purposes of this AD, a detailed 

inspection is defined as: ‘‘An intensive visual 

examination of a specific structural area, 

system, installation, or assembly to detect 

damage, failure, or irregularity. Available 

lighting is normally supplemented with a 

direct source of good lighting at intensity 

deemed appropriate by the inspector. 

Inspection aids such as mirror, magnifying 

lenses, etc., may be used. Surface cleaning 

and elaborate access procedures may be 

required.’’ 

(1) Inspect the cross member, P/N CC670– 

10572, of the MLG door lower panel for 

cracking or deformation, in accordance with 

Figure 2 of this AD. 

(2) Inspect the inner skin, P/N CC670– 

10577, of the MLG door lower panel at the 

cross member (P/N CC670–10572) for 

cracking or deformation, or pulled or missing 

fasteners, in accordance with Figure 2 of this 

AD. 

(3) Inspect the outer skin, P/N CC670– 

10574, of the MLG door lower panel at the 

cross member (P/N CC670–10572) for 

cracking or deformation, or pulled or missing 

fasteners, in accordance with Figure 2 of this 

AD. 

(4) Inspect the forward member, P/N 

CC670–10570, and aft member, P/N CC670– 

10571, of the MLG door lower panel for 

cracking or deformation, or pulled or missing 

fasteners, in accordance with Figure 3 of this 

AD. Figures 1 through 3 of this AD follow. 

BILLING CODE 4910–13–P 


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Federal Register / Vol. 77, No. 40 / Wednesday, February 29, 2012 / Rules and Regulations 12161 

BILLING CODE 4910–13–C 

(i) Restatement of Requirements of AD 2003– 

19–51, Amendment 39–13353 (68 FR 61615, 

October 29, 2003), With Revised Serial 

Numbers and Service Information: 

Repetitive Inspections 

If no cracking or deformation, or pulled or 

missing fastener, as applicable, is found 

during any inspection required by paragraph 

(h) or (i) of this AD, repeat the inspections 

thereafter at intervals not to exceed 100 flight 

cycles. 

(j) Restatement of Requirements of AD 2003– 

19–51, Amendment 39–13353 (68 FR 61615, 

October 29, 2003), With Revised Serial 

Numbers and Service Information: 

Corrective Actions 

If any cracking or deformation, or pulled or 

missing fastener, as applicable, is found 

during any inspection done in accordance 

with paragraph (h) or (i) of this AD: Before 

further flight, accomplish paragraph (j)(1), 

(j)(2), or (j)(3) of this AD. 

(1) Repair the damage in accordance with 

a method approved by either the Manager, 

New York Aircraft Certification Office (ACO), 

FAA; or Transport Canada Civil Aviation 

(TCCA) (or its delegated agent); and 

accomplish repetitive inspections in 

accordance with a method and at a repetitive 

interval approved by same. 

(2) Replace the lower panel assembly, P/N 

CC670–10520, of the affected MLG door with 

a new or serviceable lower panel assembly 

having the same P/N, according to a method 

approved by either the Manager, New York 

ACO, FAA; or TCCA (or its delegated agent). 

Repeat the inspections specified in paragraph 

(h) of this AD at intervals not to exceed 100 

flight cycles. 

Note 1 to paragraph (j)(2) of this AD: 

Guidance on replacing the lower panel 

assembly can be found in Task Cards 32–12– 

01–000–801–A01 and 32–12–01–400–801– 

A01 of the Bombardier CRJ 700/900 Series 

Regional Jet Aircraft Maintenance Manual. 

(3) Remove the lower panel assembly, P/N 

CC670–10520, of the affected MLG door, and 

accomplish paragraph (j)(3)(i) or (j)(3)(ii) of 

this AD, as applicable. 

(i) For Model CL600–2C10 (Regional Jet 

series 700 & 701) series airplanes: Revise the 

Configuration Deviation List (CDL), 

Appendix 1, of the airplane flight manual 

(AFM), to include the following limitations. 

This may be accomplished by inserting a 

copy of this AD into the CDL of the AFM. 

For Model CL600–2C10 series airplanes: If 

one or both door panel assemblies, part 

number CC670–10520, is missing: 

(1) Take-off Weight is reduced by 202.5 kg/ 

door, or 450 lb/door. 

(2) Enroute Climb Weight is reduced by 

445.5 kg/door, or 990 lb/door. 

(3) Landing Weight is reduced by 202.5 kg/ 

door, or 450 lb/door. 

(4) Fuel Consumption is increased by 

+3.42% on fuel used/door. 

(5) Cruise Airspeed is limited to not more 

than 0.78 Mach. 

(ii) For Model CL–600–2D24 (Regional Jet 

series 900) series airplanes: Revise the CDL, 

Appendix 1, of the AFM, to include the 

following limitations. This may be 

accomplished by inserting a copy of this AD 

into the CDL of the AFM. 

For Model CL600–2D24 series airplanes: If 

one or both door panel assemblies, part 

number CC670–10520, is missing: 

(1) Take-off Weight is reduced by 245 kg/ 

door, or 540 lb/door. 

(2) Enroute Climb Weight is reduced by 

551 kg/door, or 1,215 lb/door. 

(3) Landing Weight is reduced by 245 kg/ 

door, or 540 lb/door. 

(4) Fuel Consumption is increased by 

+3.42% on fuel used/door. 

(5) Cruise Airspeed is limited to not more 

than 0.78 Mach. 

(k) Restatement of Requirements of AD 

2006–14–05, Amendment 39–14676 (71 FR 

38979, July 11, 2006), With Revised Service 

Information: Inboard MLG Door Inspections 

For all airplanes on which an inspection 

has not been done in accordance with 

paragraph (h) of this AD on or before August 

15, 2006: At the applicable time specified in 

paragraph (k)(1) or (k)(2) of this AD, do the 

inspections of the left- and right-hand 

inboard MLG doors for damage, in 

accordance with Part A of the 

Accomplishment Instructions of Bombardier 


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12162 Federal Register / Vol. 77, No. 40 / Wednesday, February 29, 2012 / Rules and Regulations 

Alert Service Bulletin A670BA–32–016, 

Revision A, dated June 7, 2005, excluding 

Appendix A, dated June 2, 2005, and 

including Appendix B, dated June 2, 2005; or 

Bombardier Alert Service Bulletin A670BA– 

32–016, Revision F, dated May 14, 2010, 

excluding Appendix A, dated June 2, 2005, 

and including Appendix B, dated June 2, 

2005. Doing the inspections required by this 

paragraph terminates the actions required by 

paragraphs (g) through (j) of this AD. As of 

the effective date of this AD, use only 

Bombardier Alert Service Bulletin A670BA– 

32–016, Revision F, dated May 14, 2010, 

excluding Appendix A, dated June 2, 2005, 

and including Appendix B, dated June 2, 

2005. 

(1) For airplanes that have accumulated 

fewer than 1,500 total flight cycles as of 

August 15, 2006: Before the accumulation of 

1,000 total flight cycles, or within 50 flight 

cycles after August 15, 2006, whichever 

occurs later. 

(2) For airplanes that have accumulated 

1,500 flight cycles or more as of August 15, 

2006: Within 10 flight cycles after August 15, 

2006. 

(l) Restatement of Requirements of AD 2006– 

14–05, Amendment 39–14676 (71 FR 38979, 

July 11, 2006), With Revised Service 

Information: Inboard MLG Door Inspections 

For airplanes on which an inspection has 

been done in accordance with paragraph (h) 

of this AD on or before August 15, 2006: At 

the applicable time specified in paragraph 

(l)(1) or (l)(2) of this AD, inspect installed 

door(s) as specified in paragraph (k) of this 

AD. Doing the inspections required by this 

paragraph terminates the actions required by 

paragraphs (g) through (j) of this AD. 

(1) For airplanes that are not subject to an 

approved alternative method of compliance 

(AMOC) that extends the inspection interval 

to 450 flight cycles: Within 100 flight cycles 

since the last inspection done in accordance 

with paragraph (h) of this AD. 

(2) For airplanes that are subject to an 

approved AMOC that extends the inspection 

interval to 450 flight cycles: At the earlier of 

the times specified in paragraphs (l)(2)(i) and 

(l)(2)(ii) of this AD: 

(i) Within 450 flight cycles since the last 

inspection done in accordance with 

paragraph (h) of this AD. 

(ii) Within 100 flight cycles since the last 

inspection done in accordance with 

paragraph (h) of this AD, or within 50 cycles 

after August 15, 2006, whichever occurs 

later. 

(m) Restatement of Requirements of AD 

2006–14–05, Amendment 39–14676 (71 FR 

38979, July 11, 2006), With Revised Service 

Information: Repetitive Inspections 

If no damage is found during any 

inspection done in accordance with 

paragraph (k) of this AD, repeat the 

inspections specified in paragraph (k) of this 

AD thereafter at intervals not to exceed 100 

flight cycles. 

(n) Restatement of Requirements of AD 

2006–14–05, Amendment 39–14676 (71 FR 

38979, July 11, 2006), With Revised Service 

Information: Corrective Action—Replace or 

Remove MLG Door 

If any damage is found during any 

inspection done in accordance with 

paragraph (k) of this AD, before further flight, 

do the actions in paragraph (n)(1) or (n)(2) of 

this AD. Repeat the inspections specified in 

paragraph (k) of this AD thereafter at 

intervals not to exceed 100 flight cycles. 

(1) Replace the inboard MLG door with a 

new or repaired door in accordance with Part 

B of the Accomplishment Instructions of the 

Bombardier Alert Service Bulletin A670BA– 

32–016, Revision A, dated June 7, 2005, 

excluding Appendix A, dated June 2, 2005, 

and including Appendix B, dated June 2, 

2005; or Bombardier Alert Service Bulletin 

A670BA–32–016, Revision F, dated May 14, 

2010, excluding Appendix A, dated June 2, 

2005, and including Appendix B, dated June 

2, 2005; except where those service bulletins 

specify to contact the manufacturer for repair 

if no generic repair engineering order (REO) 

is available, before further flight, repair using 

a method approved by either the Manager, 

New York ACO, FAA; or TCCA (or its 

delegated agent). As of the effective date of 

this AD, use only Bombardier Alert Service 

Bulletin A670BA–32–016, Revision F, dated 

May 14, 2010, excluding Appendix A, dated 

June 2, 2005, and including Appendix B, 

dated June 2, 2005. 

(2) Remove the inboard MLG door in 

accordance with Part B of the 

Accomplishment Instructions of the 

Bombardier Alert Service Bulletin A670BA– 

32–016, Revision A, dated June 7, 2005, 

excluding Appendix A, dated June 2, 2005, 

and including Appendix B, dated June 2, 

2005; or Bombardier Alert Service Bulletin 

A670BA–32–016, Revision F, dated May 14, 

2010, excluding Appendix A, dated June 2, 

2005, and including Appendix B, dated June 

2, 2005; and accomplish paragraph (n)(2)(i) 

or (n)(2)(ii) of this AD, as applicable. As of 

the effective date of this AD, use only 

Bombardier Alert Service Bulletin A670BA– 

32–016, Revision F, dated May 14, 2010, 

excluding Appendix A, dated June 2, 2005, 

and including Appendix B, dated June 2, 

2005. 

(i) For Model CL–600–2C10 (Regional Jet 

Series 700, 701, & 702) airplanes and Model 

CL–600–2D15 (Regional Jet Series 705) 

airplanes: Revise the Configuration Deviation 

List (CDL), Appendix 1, of the Bombardier 

Canadair Regional Jet AFM, to include the 

following limitations. This may be 

accomplished by inserting a copy of this AD 

into the CDL of the AFM. Remove any 

existing CDL limitation required by 

paragraph (j)(3)(i) of this AD from the AFM. 

For Model CL–600–2C10 (Regional Jet 

Series 700, 701, & 702) airplanes and Model 

CL–600–2D15 (Regional Jet Series 705) 

airplanes: If one or both door panel 

assemblies, part number CC670–10520, is 

missing: 

(1) Take-off Weight is reduced by 202.5 kg/ 

door, or 450 lb/door. 

(2) Enroute Climb Weight is reduced by 

445.5 kg/door, or 990 lb/door. 

(3) Landing Weight is reduced by 202.5 kg/ 

door, or 450 lb/door. 

(4) Fuel Consumption is increased by 

+2.5% on fuel used/door. 

(5) Cruise Airspeed is limited to not more 

than 0.78 Mach. 

(6) The climb ceiling obtained from the 

Flight Planning and Cruise Control Manual 

(FPCCM) must be reduced by 1,000 ft/door. 

Note 2 to paragraph (n)(2)(i) of this AD: 

When a statement with the information 

specified in paragraph (n)(2)(i) of this AD has 

been included in the general revisions of the 

AFM, the general revisions may be inserted 

into the AFM, and the copy of this AD may 

be removed from the AFM. 

(ii) For Model CL–600–2D24 (Regional Jet 

Series 900) airplanes: Revise the CDL, 

Appendix 1, of the Bombardier Canadair 

Regional Jet AFM, to include the following 

limitations. This may be accomplished by 

inserting a copy of this AD into the CDL of 

the AFM. Remove any existing CDL 

limitation required by paragraph (j)(3)(ii) of 

this AD from the AFM. 

For Model CL–600–2D24 (Regional Jet 

Series 900) airplanes: If one or both door 

panel assemblies, part number CC670–10520, 

is missing: 

(1) Take-off Weight is reduced by 245 kg/ 

door, or 540 lb/door. 

(2) Enroute Climb Weight is reduced by 

551 kg/door, or 1,215 lb/door. 

(3) Landing Weight is reduced by 245 kg/ 

door, or 540 lb/door. 

(4) Fuel Consumption is increased by 

+2.5% on fuel used/door. 

(5) Cruise Airspeed is limited to not more 

than 0.78 Mach. 

(6) The climb ceiling obtained from the 

Flight Planning and Cruise Control Manual 

(FPCCM) must be reduced by 1,000 ft/door. 

Note 3 to paragraph (n)(2)(ii) of this AD: 

When a statement with the information 

specified in paragraph (n)(2)(ii) of this AD 

has been included in the general revisions of 

the AFM, the general revisions may be 

inserted into the AFM, and the copy of this 

AD may be removed from the AFM. 

(o) Restatement of Requirements of AD 

2006–14–05, Amendment 39–14676 (71 FR 

38979, July 11, 2006), With Revised Service 

Information: Revise CDL 

For airplanes on which the door(s) have 

been removed in accordance with paragraph 

(j)(3) of this AD: Within 30 days after August 

15, 2006, do the revision specified in 

paragraph (n)(2)(i) or (n)(2)(ii) of this AD, as 

applicable, and remove any revision required 

by paragraph (j)(3)(i) or (j)(3)(ii) of this AD. 

(p) Restatement of Requirements of AD 

2006–14–05, Amendment 39–14676 (71 FR 

38979, July 11, 2006), With Revised Service 

Information: No Reporting Required 

Although Bombardier Alert Service 

Bulletin A670BA–32–016, Revision A, dated 

June 7, 2005, excluding Appendix A, dated 

June 2, 2005, and including Appendix B, 

dated June 2, 2005; and Bombardier Alert 

Service Bulletin A670BA–32–016, Revision 

F, dated May 14, 2010, excluding Appendix 

A, dated June 2, 2005, and including 

Appendix B, dated June 2, 2005; specify to 

submit certain information to the 

manufacturer, this AD does not include that 

requirement. 


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Federal Register / Vol. 77, No. 40 / Wednesday, February 29, 2012 / Rules and Regulations 12163 

(q) Restatement of Requirements of AD 

2006–14–05, Amendment 39–14676 (71 FR 

38979, July 11, 2006), With Revised Service 

Information: Credit for Previous Actions 

This paragraph provides credit for actions 

required by paragraphs of (g) through (q) of 

this AD, if those actions were performed 

before August 15, 2006 (the effective date of 

AD 2006–14–05, Amendment 39–14767 (71 

FR 38979, July 11, 2006), using Bombardier 

Alert Service Bulletin A670BA–32–016, 

dated June 2, 2005. 

(r) New Requirements of This AD: 

Terminating Modification for MLG Door 

Configuration 

Within 6,000 flight hours after the effective 

date of this AD, modify the MLG door, in 

accordance with the Accomplishment 

Instructions of Bombardier Service Bulletin 

670BA–32–017, Revision C, dated May 14, 

2010. Doing this modification terminates the 

requirements of this AD. 

(s) New Requirements of This AD: Credit for 

Previous Actions 

This paragraph provides credit for the 

modification of the MLG door required by 

paragraph (r) of this AD, if the modification 

was performed before the effective date of 

this AD using Bombardier Service Bulletin 

670BA–32–017, dated July 24, 2006; Revision 

A, dated September 26, 2006; or Revision B, 

dated July 31, 2008; as applicable. 

(t) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): 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. 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 

2006–14–05, Amendment 39–14676 (71 FR 

38979, July 11, 2006), are acceptable for 

compliance with 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. 

(u) Related Information 

Refer to MCAI TCCA Airworthiness 

Directive CF–2003–23R3, dated May 21, 

2010, and the following service information 

for related information: 

(1) Bombardier Alert Service Bulletin 

A670BA–32–016, Revision F, dated May 14, 

2010, excluding Appendix A, dated June 2, 

2005, and including Appendix B, dated June 

2, 2005. 

(2) Bombardier Service Bulletin 670BA– 

32–017, Revision C, dated May 14, 2010. 

(v) Material Incorporated by Reference 

(1) You must use the following service 

information to do the actions required by this 

AD, unless the AD specifies otherwise. The 

Director of the Federal Register approved the 

incorporation by reference (IBR) of the 

following service information under 5 U.S.C. 

552(a) and 1 CFR part 51: 

(i) Bombardier Service Bulletin 670BA–32– 

017, Revision C, dated May 14, 2010. 

(ii) Bombardier Alert Service Bulletin 

A670BA–32–016, Revision F, dated May 14, 

2010, excluding Appendix A, dated June 2, 

2005, and including Appendix B, dated June 

2, 2005. 

(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; email 

thd.crj@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. 

(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/ 

cfr/ibr_locations.html. 

Issued in Renton, Washington, on January 

27, 2012. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2012–4449 Filed 2–28–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0912; Directorate 

Identifier 2011–NM–035–AD; Amendment 

39–16962; AD 2012–04–06] 

RIN 2120–AA64 

Airworthiness Directives; 328 Support 

Services GmbH (Type Certificate 

Previously Held by AvCraft Aerospace 

GmbH; Fairchild Dornier GmbH; 

Dornier Luftfahrt GmbH) Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all 328 

Support Services GmbH (Type 

Certificate Previously Held by AvCraft 

Aerospace GmbH; Fairchild Dornier 

GmbH; Dornier Luftfahrt GmbH) Model 

328–100 airplanes. This proposed AD 

was prompted by several runway 

excursion incidents and a single 

accident where the power lever could 

not be operated as intended during the 

landing roll-out on Model Dornier 328– 

100 airplanes. This proposed AD would 

require a modification of the engine 

control box assembly. We are proposing 

this AD to prevent runway excursion, 

which could result in damage to the 

airplane and injury to the occupants. 

DATES: This AD becomes effective April 

4, 2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of April 4, 2012. 

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: Tom 

Groves, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone (425) 227–1503; 

fax (425) 227–1149. 

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 August 31, 2011 (76 FR 

54145). That NPRM proposed to correct 

an unsafe condition for the specified 

products. The MCAI states: 

Several runway excursion incidents and a 

single accident have occurred in the past 

with Dornier 328–100 aeroplanes, where the 

power lever could not be operated as 

intended during the landing roll-out. * * * 

Recurrence of such an event under similar 

conditions, if not corrected, could result in 

further cases of runway excursion, possibly 

resulting in damage to the aeroplane and 

injury to the occupants. 

A modification to the power lever control 

box [i.e., engine control box assembly] has 

been designed to prevent further power lever 

handling difficulties. 

For the reasons described above, this 

[EASA] AD requires a modification of the 

power lever control box as a retrofit for the 

entire fleet of 328–100 aeroplanes. 

The required actions also include 

revising the airplane flight manual 


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