6522 Federal Register / Vol. 77, No. 26 / Wednesday, February 8, 2012 / Proposed Rules 

properly, in accordance with paragraph 

2.C.(5) of the Accomplishment Instructions of 

BAE SYSTEMS (OPERATIONS) LIMITED 

Modification Service Bulletin SB.26–077– 

36250A.B, Revision 4, dated January 7, 2011. 

(i) Squib connector WB7P1 (S1446–004A) 

and cartridge P/N 446307. 

(ii) Squib connector WB7P2 (S1446–004D) 

and squib P/N 446290. 

(4) Modify the wiring loom to squib 

connector WB7P2, in accordance with 

paragraphs 2.C.(6)(a) and 2.C.(6)(c) of the 

Accomplishment Instructions of BAE 

SYSTEMS (OPERATIONS) LIMITED 

Modification Service Bulletin SB.26–077– 

36250A.B, Revision 4, dated January 7, 2011. 

(5) Modify the wiring loom to squib 

connector WB7P1, in accordance with 

paragraph 2.C.(6)(b) of the Accomplishment 

Instructions of BAE SYSTEMS 

(OPERATIONS) LIMITED Modification 

Service Bulletin SB.26–077–36250A.B, 

Revision 4, dated January 7, 2011. 

(6) Install modification HCM36250B, in 

accordance with paragraph 2.C.(7) of the 

Accomplishment Instructions of BAE 

SYSTEMS (OPERATIONS) LIMITED Service 

Bulletin SB.26–077–36250A.B, Revision 4, 

dated January 7, 2011. 

Note 1 to paragraph (g): Guidance for test 

and close-up procedures can be found in 

paragraphs 2.D. and 2.E. of the 

Accomplishment Instructions of BAE 

SYSTEMS (OPERATIONS) LIMITED 

Modification Service Bulletin SB.26–077– 

36250A.B, Revision 4, dated January 7, 2011. 

(h) Credit for Actions Accomplished in 

Accordance With Previous Service 

Information 

Installing modification HCM36250A in 

accordance with the service information 

specified in paragraphs (h)(1), (h)(2), (h)(3), 

or (h)(4) of this AD before the effective date 

of this AD is acceptable for compliance with 

the actions specified in paragraphs (g)(1), 

(g)(2), (g)(3), (g)(4), and (g)(5) of this AD. 

(1) BAE SYSTEMS (OPERATIONS) 

LIMITED Modification Service Bulletin 

SB.26–077–36250A, dated September 4, 

2009. 

(2) BAE SYSTEMS (OPERATIONS) 

LIMITED Modification Service Bulletin 

SB.26–077–36250A, Revision 1, dated 

September 11, 2009. 

(3) BAE SYSTEMS (OPERATIONS) 

LIMITED Modification Service Bulletin 

SB.26–077–36250A.B, Revision 2, dated 

October 14, 2010. 

(4) BAE SYSTEMS (OPERATIONS) 

LIMITED Modification Service Bulletin 

SB.26–077–36250A.B, Revision 3, dated 

November 23, 2010. 

(i) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, FAA, has the authority to approve 

AMOCs for this AD, if requested using the 

procedures found in 14 CFR 39.19. In 

accordance with 14 CFR 39.19, send your 

request to your principal inspector or local 

Flight Standards District Office, as 

appropriate. If sending information directly 

to the International Branch, send it to Attn: 

Todd Thompson, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA 1601 Lind Avenue 

SW., Renton, Washington 98057–3356; 

telephone (425) 227–1175; fax (425) 227– 

1149. Information may be emailed to: 

9-ANM-116-AMOC-REQUESTS@faa.gov. 

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. 

(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. 

(j) Related Information 

Refer to MCAI European Aviation Safety 

Agency Airworthiness Directive 2011–0065, 

dated April 7, 2011; and BAE SYSTEMS 

(OPERATIONS) LIMITED Modification 

Service Bulletin SB.26–077–36250A.B, 

Revision 4, dated January 7, 2011; for related 

information. 

Issued in Renton, Washington, on January 

26, 2012. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2012–2908 Filed 2–7–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0105; Directorate 

Identifier 2011–NM–123–AD] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for certain 

The Boeing Company Model 777 

airplanes. This proposed AD was 

prompted by reports of fractured and 

missing latch pin retention bolts that 

secure the latch pins on the forward 

cargo door. This proposed AD would 

require repetitive detailed inspections 

for fractured or missing latch pin 

retention bolts, replacement of existing 

titanium bolts with new Inconel bolts, 

and related investigative and corrective 

actions if necessary. We are proposing 

this AD to detect and correct fractured 

and missing latch pin retention bolts, 

which could result in potential 

separation of the cargo door from the 

airplane and catastrophic 

decompression of the airplane. 

DATES: We must receive comments on 

this proposed AD by March 26, 2012. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, 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: Deliver to Mail 

address above between 9 a.m. and 

5 p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this proposed 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; email 

me.boecom@boeing.com; Internet 

https://www.myboeingfleet.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 proposed AD, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket Office 

(phone: (800) 647–5527) is in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

FOR FURTHER INFORMATION CONTACT: Ana 

Martinez Hueto, Aerospace Engineer, 

Cabin Safety and Environmental 

Systems Branch, ANM–150S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; phone: (425) 917–6592; 

fax: (425) 917–6590; email: 

ana.m.hueto@faa.gov. 


pmangrum on DSK3VPTVN1PROD with PROPOSALS-1
Federal Register / Vol. 77, No. 26 / Wednesday, February 8, 2012 / Proposed Rules 6523 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposal. Send your comments to 

an address listed under the ADDRESSES

section. Include ‘‘Docket No. FAA– 

2012–0105; Directorate Identifier 2011– 

NM–123–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 because of 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 

We have received reports of fractured 

and missing latch pin retention bolts 

that secure the latch pins on the forward 

cargo door. Two adjacent latch pins that 

migrate from their position, or are 

broken in close proximity, are not able 

to hold the door closed for the design 

loads. Fractured and missing latch pin 

retention bolts, if not detected and 

corrected, could result in potential 

separation of the cargo door from the 

airplane and catastrophic 

decompression of the airplane. 

Relevant Service Information 

We reviewed Boeing Alert Service 

Bulletin 777–52A0038, Revision 1, 

dated June 24, 2010. This service 

information describes procedures for 

repetitive detailed inspections for 

fractured or missing latch pin retention 

bolts, and related investigative and 

corrective actions if necessary. 

Related investigative actions include 

measuring the migration distance of the 

latch pins; a detailed inspection for any 

crack or surface depression of the latch 

pin retention bolt hole; a detailed 

inspection for any crack or damage of 

the lower sill of the forward large cargo 

door, fuselage frames, internal and 

external skin of the fuselage, cargo door 

frames, mid-span latch cam (if 

installed), and main cam latch 

mechanisms; and a detailed inspection 

for any cut, crack, or damage of the 

main cam latch of the cargo door. 

Corrective actions include contacting 

Boeing for repair instructions; repairing; 

changing the installed bolt head 

direction; applying the specified torque 

to the retention bolts to check for loose 

bolts; replacing existing latch pin 

retention bolts made of titanium with 

new Inconel bolts; replacing the latch 

pin fitting assembly; repairing the lower 

sill of the forward large cargo door, 

fuselage frames, internal and external 

skin of the fuselage, cargo door frames, 

mid-span latch cam, and main cam latch 

mechanisms; and replacing the cargo 

door main cam latch, if necessary. 

Replacing latch pin retention bolts 

made of titanium with new Inconel 

bolts, if accomplished, would eliminate 

the need for repetitive inspections for 

that area only. 

For the detailed inspections for 

fractured or missing latch pin retention 

bolts, the service information specifies 

an initial compliance time of within 12 

months after the Revision 1 issue date, 

and a repetitive interval of 1,000 flight 

cycles. 

FAA’s Determination 

We are proposing this AD because we 

evaluated all the relevant information 

and determined the unsafe condition 

described previously is likely to exist or 

develop in other products of these same 

type designs. 

Proposed AD Requirements 

This proposed AD would require 

accomplishing the actions specified in 

the service information described 

previously. 

Differences Between the Proposed AD 

and the Service Information 

Boeing Alert Service Bulletin 777– 

52A0038, Revision 1, dated June 24, 

2010, specifies to contact the 

manufacturer for instructions on how to 

repair certain conditions, but this 

proposed AD would require repairing 

those conditions in one of the following 

ways: 

• In accordance with a method that 

we approve; or 

• Using data that meet the 

certification basis of the airplane, and 

that have been approved by the Boeing 

Commercial Airplanes Organization 

Designation Authorization (ODA) whom 

we have authorized to make those 

findings. 

Costs of Compliance 

We estimate that this proposed AD 

affects 148 airplanes of U.S. registry. 

We estimate the following costs to 

comply with this proposed AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

Inspection ....................................... 1 work-hour × $85 per hour = $85 .................................. $0 $85 $12,580 

We estimate the following costs to do 

any necessary repairs that would be 

required based on the results of the 

proposed inspection. We have no way of 

determining the number of aircraft that 

might need these repairs: 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per 

product 

Cross-bolt replacement ............................ 2 work-hours × $85 per hour = $170 ............................................... $50 $220 

We estimate the following costs to do 

any necessary repairs that would be 

required based on the results of the 

proposed inspection. We have no way of 

determining the number of aircraft that 

might need these repairs: 

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 


pmangrum on DSK3VPTVN1PROD with PROPOSALS-1
6524 Federal Register / Vol. 77, No. 26 / Wednesday, February 8, 2012 / Proposed Rules 

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), 

(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. 

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 adding 

the following new airworthiness 

directive (AD): 

The Boeing Company: Docket No. FAA– 

2012–0105; Directorate Identifier 2011– 

NM–123–AD. 

(a) Comments Due Date 

We must receive comments by March 26, 

2012. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to The Boeing Company 

Model 777–200, –200LR, –300, –300ER, and 

777F series airplanes; certificated in any 

category; as identified in Boeing Alert 

Service Bulletin 777–52A0038, Revision 1, 

dated June 24, 2010. 

(d) Subject 

Joint Aircraft System Component (JASC)/ 

Air Transport Association (ATA) of America 

Code 52, Doors. 

(e) Unsafe Condition 

This AD was prompted by reports of 

fractured and missing latch pin retention 

bolts that secure the latch pins on the 

forward cargo door. We are issuing this AD 

to detect and correct fractured and missing 

latch pin retention bolts, which could result 

in potential separation of the cargo door from 

the airplane and catastrophic decompression 

of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspect Retention Bolt of Latch Pin 

Fittings No. 1 Through No. 8 

At the applicable times specified in 

paragraph 1.E., ‘‘Compliance,’’ of Boeing 

Alert Service Bulletin 777–52A0038, 

Revision 1, dated June 24, 2010, except as 

specified in paragraph (i) of this AD: Do a 

detailed inspection for fractured and/or 

missing latch pin retention bolts of the latch 

pin fittings of the lower sill of the forward 

large cargo door, and do all applicable related 

investigative and corrective actions, in 

accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

777–52A0038, Revision 1, dated June 24, 

2010, except as provided by paragraph (h) of 

this AD. Do all applicable related 

investigative and corrective actions at the 

applicable times specified in paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 777–52A0038, Revision 1, dated 

June 24, 2010. Repeat the inspection 

thereafter at the applicable time specified in 

paragraph 1.E., ‘‘Compliance,’’ of Boeing 

Alert Service Bulletin 777–52A0038, 

Revision 1, dated June 24, 2010, except as 

specified in paragraph (j) of this AD. 

(h) Repair 

If any cut, crack, or damage is found during 

any inspection required by this AD, and 

Boeing Alert Service Bulletin 777–52A0038, 

Revision 1, dated June 24, 2010, specifies to 

contact Boeing for appropriate action: Before 

further flight, repair the cut, crack, or damage 

in accordance with a method approved by 

the Manager, Seattle, Aircraft Certification 

Office (ACO), FAA. For a repair method to 

be approved, the repair must meet the 

certification basis of the airplane, and the 

approval must specifically refer to this AD. 

(i) Exception to Compliance Time 

Where Boeing Alert Service Bulletin 777– 

52A0038, Revision 1, dated June 24, 2010, 

specifies a compliance time after the date on 

that service bulletin, this AD requires 

compliance within the specified compliance 

time after the effective date of this AD. 

(j) Optional Terminating Action for 

Repetitive Inspections 

Replacing latch pin retention bolts made of 

titanium with new Inconel bolts, in 

accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

777–52A0038, Revision 1, dated June 24, 

2010, terminates the repetitive inspections 

required by paragraph (g) of this AD at 

Stations 509.10, 522.75, 537.50, 554.30, 

562.90, 579.70, 591.25, and 604.90, latch pin 

fittings No. 1 through No. 8. 

(k) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle Aircraft 

Certification Office (ACO), FAA, has the 

authority to approve AMOCs for this AD, if 

requested using the procedures found in 14 

CFR 39.19. In accordance with 14 CFR 39.19, 

send your request to your principal inspector 

or local Flight Standards District Office, as 

appropriate. If sending information directly 

to the manager of the ACO, send it to the 

attention of the person identified in the 

Related Information section of this AD. 

Information may be emailed to: 9-ANMSeattle-ACO-AMOC-Requests@faa.gov. 

(2) 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. 

(l) Related Information 

(1) For more information about this AD, 

contact Ana Martinez Hueto, Aerospace 

Engineer, Cabin Safety and Environmental 

Systems Branch, ANM–150S, FAA, Seattle 

Aircraft Certification Office, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

phone: (425) 917–6592; fax: (425) 917–6590; 

email: ana.m.hueto@faa.gov. 

(2) 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; email me.boecom@boeing.com; Internet 

https://www.myboeingfleet.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. 


pmangrum on DSK3VPTVN1PROD with PROPOSALS-1
Federal Register / Vol. 77, No. 26 / Wednesday, February 8, 2012 / Proposed Rules 6525 

Issued in Renton, Washington on January 

27, 2012. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2012–2911 Filed 2–7–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–1089; Directorate 

Identifier 2011–NM–110–AD] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier, 

Inc., Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Supplemental notice of 

proposed rulemaking (NPRM); 

reopening of comment period. 

SUMMARY: We are revising an earlier 

proposed airworthiness directive (AD) 

for certain Bombardier, Inc. Model BD– 

100–1A10 (Challenger 300) airplanes. 

That NPRM proposed an inspection to 

determine if a certain oxygen cylinder 

and regulator assembly (CRA) is 

installed and the replacement of 

affected oxygen CRAs. That NPRM was 

prompted by reports of deformation 

found at the neck of the pressure 

regulator body on the oxygen CRA. This 

action revises that NPRM by revising the 

compliance times. We are proposing 

this supplemental NPRM to prevent 

elongation of the pressure regulator 

neck, which could result in rupture of 

the oxygen cylinder, and in the case of 

cabin depressurization, oxygen not 

being available when required. Since 

these actions impose an additional 

burden over that proposed in the NPRM, 

we are reopening the comment period to 

allow the public the chance to comment 

on these proposed changes. 

DATES: We must receive comments on 

this proposed AD by March 26, 2012. 

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; 

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 

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: 

Cesar Gomez, 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– 

7318; 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–2011–1089; Directorate Identifier 

2011–NM–110–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 

We proposed to amend 14 CFR part 

39 with an earlier NPRM for the 

specified products, which was 

published in the Federal Register on 

October 19, 2011 (76 FR 64857). That 

earlier NPRM proposed to require 

actions intended to address the unsafe 

condition for Model BD–100–1A10 

(Challenger 300) airplanes. 

Since that NPRM (76 FR 64857, 

October 19, 2011) was issued, we have 

determined that a revision to the 

compliance time is needed. We are 

changing the compliance time in 

paragraph (g) of this supplemental 

NPRM to ‘‘within 750 flight hours, or 6 

months after the effective date of this 

AD, whichever occurs first.’’ We have 

determined that this compliance time is 

adequate to address the unsafe 

condition. 

You may obtain further information 

by examining the MCAI in the AD 

docket. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM (76 

FR 64857, October 19, 2011), or on the 

determination of the cost to the public. 

Additional Change 

We have made minor editorial 

changes to this supplemental NPRM. 

We have determined that these minor 

editorial changes: 

• Are consistent with the intent that 

was proposed in the NPRM (76 FR 

64857, October 19, 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 64857, 

October 19, 2011). 

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. 

Certain changes described above 

expand the scope of the earlier NPRM 

(76 FR 64857, October 19, 2011). As a 

result, we have determined that it is 

necessary to reopen the comment period 

to provide additional opportunity for 


pmangrum on DSK3VPTVN1PROD with PROPOSALS-1