Federal Register / Vol. 76, No. 193 / Wednesday, October 5, 2011 / Proposed Rules 61633 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0994; Directorate 

Identifier 2010–NM–143–AD] 

RIN 2120–AA64 

Airworthiness Directives; 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 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for the 

products listed above that would 

supersede an existing AD. This 

proposed 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: 

The right-hand inboard main landing gear 

(MLG) door of a CRJ 700 departed the aircraft 

during the landing phase of flight. The door 

damaged the trailing edge flap and punctured 

the rear fuselage near the floor level. The 

aircraft landed safely. Preliminary 

investigation indicates the failure was 

initiated by fatigue of the panel structure 

near a panel hinge lug. Loss of the main 

landing gear door during flight could result 

in damage to the aircraft and injury to 

persons on the ground. 

* * * * * 

The proposed AD would require actions 

that are intended to address the unsafe 

condition described in the MCAI. 

DATES: We must receive comments on 

this proposed AD by November 21, 

2011. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: (202) 493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue, SE., Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue, SE., Washington, DC, between 

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

Friday, except Federal holidays. 

For service information identified in 

this proposed 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.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 Operations office between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains this proposed AD, 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. 

FOR FURTHER INFORMATION CONTACT: 

Daniel Parrillo, Program Manager, 

Continuing Operational Safety, FAA, 

New York Aircraft Certification Office 

(ACO), 1600 Stewart Avenue, Suite 410, 

Westbury, New York 11590; telephone 

516–228–7300; fax (516) 794–5531. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2011–0994; Directorate Identifier 

2010–NM–143–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD based on those comments. 

We will post all comments we 

receive, without change, to http:// 

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this proposed AD. 

Discussion 

On June 28, 2006, we issued AD 

2006–14–05, Amendment 39–14676 (71 

FR 38979, July 11, 2006). That AD 

required actions intended to address an 

unsafe condition on the products listed 

above. 

Since we issued AD 2006–14–05, 

Amendment 39–14676 (71 FR 38979, 

July 11, 2006), we have determined it is 

necessary to require a new modification 

of the MLG door configuration. We have 

also removed airplanes equipped with 

the new MLG door during production 

from the applicability of this NPRM. 

Transport Canada Civil Aviation 

(TCCA), which is the aviation authority 

for Canada, has issued Canadian 

Airworthiness Directive CF–2003–23R3, 

dated May 21, 2010 (referred to after 

this as ‘‘the MCAI’’), to correct an unsafe 

condition for the specified products. 

The MCAI states: 

The right-hand inboard main landing gear 

(MLG) door of a CRJ 700 departed the aircraft 

during the landing phase of flight. The door 

damaged the trailing edge flap and punctured 

the rear fuselage near the floor level. The 

aircraft landed safely. Preliminary 

investigation indicates the failure was 

initiated by fatigue of the panel structure 

near a panel hinge lug. Loss of the main 

landing gear door during flight could result 

in damage to the aircraft and injury to 

persons on the ground. 

Subsequent to the issuance of Revision 1 

of this directive, Transport Canada (TC) 

approved an alternate means of compliance 

(AMOC), AARDG 2004/A007, to allow 

extension of the repeat inspection interval 

when inboard MLG doors have incorporated 

certain repairs or modifications. 

Subsequent to the issuance of the TC 

AMOC AARDG 2004/A007, an inboard MLG 

door departed from an aircraft operating 

under an AMOC equivalent to TC AMOC 

AARDG 2004/007. As a result of this 

incident, this directive was revised to 

Revision 2 to introduce additional inspection 

requirements according to Bombardier Alert 

Service Bulletin A670–32–016. In addition, 

Revision 2 also eliminated escalation of the 

repeat inspection interval allowed in TC 

AMOC AARDG 2004/007 and revised the 

aircraft applicability to add a new aircraft 

model. 

Since the issuance of Revision 2 of this 

directive, TC approved an AMOC, AARDG 

2006–A051, to allow the installation of a new 

modified MLG door configuration and to 

perform alternative inspection. Service 

history shows that this new modified MLG 

door configuration resolves the safety 

concerns associated with this directive. 

Revision 3 of this directive mandates the 

incorporation of the new modified MLG door 

configuration in accordance with Bombardier 

Aerospace Service Bulletin (SB) 670BA–32– 

017 as the terminating action. In addition, 

this revision restricts the applicability to 

aircraft not equipped with the new modified 

MLG door configuration at delivery. 

You may obtain further information by 

examining the MCAI in the AD docket. 

We have also revised paragraph (j)(2) 

of this NPRM to remove reference to 

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. We 


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added Note 2 to this NPRM to refer to 

these tasks cards as additional sources 

of guidance for replacing the lower 

panel assembly. Operators may contact 

the International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

for information regarding the use of the 

task cards for replacing the lower panel 

assembly, as required by paragraph (j)(2) 

of this AD. 

Relevant Service Information 

Bombardier has issued Alert Service 

Bulletin A670BA–32–016, Revision F, 

dated May 14, 2010, including 

Appendices A and B, dated June 2, 

2005; and Service Bulletin 670BA–32– 

017, Revision C, dated May 14, 2010. 

The actions described in this service 

information are intended to correct the 

unsafe condition identified in the 

MCAI. 

FAA’s Determination and Requirements 

of This Proposed AD 

This product has been approved by 

the aviation authority of another 

country, and is approved for operation 

in the United States. Pursuant to our 

bilateral agreement with the State of 

Design Authority, we have been notified 

of the unsafe condition described in the 

MCAI and service information 

referenced above. We are proposing this 

AD because we evaluated all pertinent 

information and determined an unsafe 

condition exists and is likely to exist or 

develop on other products of the same 

type design. 

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 proposed 

different actions in this AD from those 

in the MCAI in order to follow FAA 

policies. Any such differences are 

highlighted in a NOTE within the 

proposed AD. 

Costs of Compliance 

Based on the service information, we 

estimate that this proposed AD would 

affect 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 proposed AD take about 3 workhours 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 would take about 

115 work-hours per product to comply 

with the new basic requirements of this 

proposed AD. The average labor rate is 

$85 per work-hour. Required parts 

would 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 proposed AD on U.S. operators to be 

$2,150,500, or $9,775 per product. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. ‘‘Subtitle VII: 

Aviation Programs,’’ describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in ‘‘Subtitle VII, 

Part A, Subpart III, Section 44701: 

General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We determined that this proposed AD 

would not have federalism implications 

under Executive Order 13132. This 

proposed AD would 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 proposed regulation: 

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 proposed AD and placed it in the 

AD docket. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 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 Amendment 39–14676 (71 FR 

38979, July 11, 2006) and adding the 

following new AD: 

Bombardier, Inc.: Docket No. FAA–2011– 

0994; Directorate Identifier 2010–NM– 

143–AD. 

Comments Due Date 

(a) We must receive comments by 

November 21, 2011. 

Affected ADs 

(b) This AD supersedes AD 2006–14–05, 

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

2006). 

Applicability 

(c) 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. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 32: Landing gear. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

The right-hand inboard main landing gear 

(MLG) door of a CRJ 700 departed the aircraft 

during the landing phase of flight. The door 

damaged the trailing edge flap and punctured 

the rear fuselage near the floor level. The 

aircraft landed safely. Preliminary 

investigation indicates the failure was 

initiated by fatigue of the panel structure 

near a panel hinge lug. Loss of the main 

landing gear door during flight could result 

in damage to the aircraft and injury to 

persons on the ground. 

* * * * * 


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Compliance 

(f) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified, unless the 

actions have already been done. 

Restatement of Requirements of AD 2003– 

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

October 29, 2003), With Revised Serial 

Numbers and Service Information 

Initial Compliance Time 

(g) 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. 

Inspections 

(h) 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. 

Note 1: 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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BILLING CODE 4910–13–C 

Repetitive Inspections 

(i) 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. 

Corrective Actions 

(j) 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). 


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Repeat the inspections specified in paragraph 

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

flight cycles. 

Note 2: For guidance on replacing the 

lower panel assembly, refer to 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.’’ 

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 

(k) 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 righthand inboard MLG doors for damage, in 

accordance with Part A of the 

Accomplishment Instructions of 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. 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. 

(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) 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) 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. 

Corrective Action—Replace or Remove MLG 

Door 

(n) 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. 

(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. 

(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 3: 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. 


jlentini on DSK4TPTVN1PROD with PROPOSALS
61638 Federal Register / Vol. 76, No. 193 / Wednesday, October 5, 2011 / Proposed Rules 

(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 4: 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. 

Revise CDL 

(o) 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. 

No Reporting Required 

(p) 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 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. 

Actions Accomplished According to 

Previous Issue of Service Bulletin 

(q) Actions accomplished before August 

15, 2006, according to Bombardier Alert 

Service Bulletin A670BA–32–016, dated June 

2, 2005, are considered acceptable for 

compliance with the corresponding actions 

of this AD. 

New Requirements of This AD 

Terminating Modification for MLG Door 

Configuration 

(r) 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. 

Credit for Actions Accomplished in 

Accordance With Previous Service 

Information 

(s) Modifying the MLG door before the 

effective date of this AD, in accordance with 

the Accomplishment Instructions of 

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; is considered 

acceptable for compliance with the 

requirements of paragraph (r) of this AD. 

FAA AD Differences 

Note 5: This AD differs from the MCAI 

and/or service information as follows: No 

differences. 

Other FAA AD Provisions 

(t) 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. 

Related Information 

(u) Refer to MCAI TCCA Airworthiness 

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

2010; 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 Bombardier Service Bulletin 

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

2010; for related information. 

Issued in Renton, Washington, on 

September 22, 2011. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2011–25571 Filed 10–4–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0995; Directorate 

Identifier 2010–NM–243–AD] 

RIN 2120–AA64 

Airworthiness Directives; 328 Support 

Services GmbH (Type Certificate 

Previously Held by AvCraft Aerospace 

GmbH; Fairchild Dornier GmbH; 

Dornier Luftfahrt GmbH) Model 328– 

100 and 328–300 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for the 

products listed above. This proposed 

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: 

Based on in-service experience, the System 

Safety Analyses for the Flight Controls have 

been reviewed and their conclusions have 

been accepted during the latest Candidate 

Maintenance Coordination Committee 

meeting. 

This review resulted in reduced inspection 

intervals, specifically for the flight controls 

tab-to-actuator linkage [certification 

maintenance requirements] CMR** repetitive 

inspections, which have been identified as 

mandatory actions for continued 

airworthiness. 

Failure of these components or their 

constituent parts could lead to reduced 

control of the aeroplane. 

* * * * * 

The proposed AD would require actions 

that are intended to address the unsafe 

condition described in the MCAI. 

DATES: We must receive comments on 

this proposed AD by November 21, 

2011. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: (202) 493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue, SE., Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–40, 1200 New Jersey 

Avenue, SE., Washington, DC, between 

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

Friday, except Federal holidays. 

For service information identified in 

this proposed AD, contact 328 Support 

Services GmbH, Global Support Center, 

P.O. Box 1252, D–82231 Wessling, 

Federal Republic of Germany; 

telephone: +49 8153 88111 6666; fax: 

+49 8153 88111 6565; e-mail: 

gsc.op@328support.de; Internet: http:// 

www.328support.de. 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 


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