Federal Register / Vol. 78, No. 70 / Thursday, April 11, 2013 / Proposed Rules 21573 

(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): Docket No. FAA–2013– 

0304; Directorate Identifier 2013–NM– 

005–AD. 

(a) Comments Due Date 

We must receive comments by May 

28, 2013. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to The Boeing 

Company Model 747–400, –400D, and 

–400F series airplanes, certificated in 

any category, as identified in Boeing 

Alert Service Bulletin 747–25A3613, 

dated June 22, 2012. 

(d) Subject 

Joint Aircraft System Component 

(JASC)/Air Transport Association (ATA) 

of America Code 25: Equipment/ 

Furnishings. 

(e) Unsafe Condition 

This AD was prompted by a report 

indicating that water leakage into the 

main deck cargo wire integration unit 

(WIU) was found. The water flowed 

from the drip shield through disbonded 

floor seams into the aft main equipment 

center (MEC) drip shield gutter, then 

onto the WIU. We are issuing this AD 

to prevent water penetration into the 

MEC, which could result in the loss of 

flight critical systems. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless 

already done. 

(g) Removal/Cleaning/Inspection/Repair 

if Necessary/Installations 

Within 24 months after the effective 

date of this AD: Do the actions specified 

in paragraphs (g)(1) and (g)(2) of this 

AD, in accordance with the 

Accomplishment Instructions of Boeing 

Alert Service Bulletin 747–25A3613, 

dated June 22, 2012. 

(1) Remove the cargo liner support, 

clean the aft MEC drip shield gutter, and 

do a general visual inspection for 

disbonded seams; repair before further 

flight if any seam disbonding is found. 

(2) Install a fiberglass reinforcement 

overcoat to the top surface of the aft 

MEC drip shield gutters, and install a 

cargo liner support. 

(h) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle ACO, 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-ANM-Seattle-ACO-AMOCRequests@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. 

(3) An AMOC that provides an 

acceptable level of safety may be used 

for any repair required by this AD if it 

is approved by the Boeing Commercial 

Airplanes Organization Designation 

Authorization (ODA) that has been 

authorized by the Manager, Seattle ACO 

to make those findings. 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) Related Information 

(1) For more information about this 

AD, contact Francis Smith, Aerospace 

Engineer, Cabin Safety and 

Environmental Systems Branch, ANM– 

150S, FAA, Seattle Aircraft Certification 

Office, 1601 Lind Avenue SW., Renton, 

Washington 98057–3356; telephone 

(425) 917–6596; fax (425) 917–6590; 

email francis.smith@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; 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. 

Issued in Renton, Washington, on March 

29, 2013. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2013–08451 Filed 4–10–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0298; Directorate 

Identifier 2012–NM–175–AD] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier, 

Inc. 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 

Bombardier, Inc. Model DHC–8–102, 

–103, –106, –201, –202, –301, –311, and 

–315 airplanes. This proposed AD was 

prompted by reports of dual alternating 

current (AC) generator failure during 

flight. The failure was attributed to wire 

chafing along the wing lower flap 

shroud. This proposed AD would 

require revising the maintenance 

program to incorporate certain tasks for 

the electrical wiring interconnection 

system inspection program. We are 

proposing this AD to prevent failure of 

both AC generators due to wire chafing, 

which could result in loss of power to 

the anti-icing heaters for the elevator 

horn, engine inlet, and propeller, and 

consequent ice accumulation in these 

areas, which could adversely affect the 

controllability of the airplane. 

DATES: We must receive comments on 

this proposed AD by May 28, 2013. 

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. 


TKELLEY on DSK3SPTVN1PROD with PROPOSALS
21574 Federal Register / Vol. 78, No. 70 / Thursday, April 11, 2013 / Proposed Rules 

• 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 Bombardier, 

Inc., Q-Series Technical Help Desk, 123 

Garratt Boulevard, Toronto, Ontario 

M3K 1Y5, Canada; telephone 416–375– 

4000; fax 416–375–4539; email 

thd.qseries@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: 

Assata Dessaline, Aerospace Engineer, 

Avionics and Services Branch, ANE– 

172, FAA, New York Aircraft 

Certification Office (ACO), 1600 Stewart 

Avenue, Suite 410, Westbury, New York 

11590; telephone (516) 228–7301; fax 

(516) 794–5531. 

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– 

2013–0298; Directorate Identifier 2012– 

NM–175–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 

Transport Canada Civil Aviation 

(TCCA), which is the aviation authority 

for Canada, has issued Canadian 

Airworthiness Directive CF–2012–25, 

dated August 28, 2012 (referred to after 

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

condition for the specified products. 

The MCAI states: 

There have been several reported 

occurrences of dual [alternating current] AC 

Generator failure during flight, resulting in 

the loss of the variable frequency AC System. 

Investigations revealed wire chafing along 

the wing lower flap shroud due to sagging 

wiring harnesses resting on the support 

structure, missing teflon tape at the fairlead 

locations, and missing grommets. Chafed 

wires may lead to arcing, local overheating, 

and AC generator failure. The AC generators 

provide power to the anti-icing heaters, 

including elevator horn heater, engine inlet 

heater and propeller heater. Failure of both 

AC generators would result in the loss of 

these systems and poses a safety concern. 

This [Canadian] AD mandates the 

inspection and rectification of the wiring 

harness installations along the centre wing 

lower flap shroud. 

Required actions include revising the 

maintenance program by incorporating 

electrical wiring interconnection system 

inspection program tasks. 

Relevant Service Information 

Bombardier, Inc. has issued the 

following service information: 

• de Havilland Dash 8 Series 100 

Maintenance Task Card 531X1, Revision 

25, in Section 8, Electrical Wiring 

Interconnection System Inspection 

Program, of Part 1, Maintenance Review 

Board Report, of the Bombardier 

DHC–8 Maintenance Program Manual 

PSM 1–8–7, dated February 20, 2012. 

• de Havilland Dash 8 Series 100 

Maintenance Task Card 631X1, Revision 

25, in Section 8, Electrical Wiring 

Interconnection System Inspection 

Program, of Part 1, Maintenance Review 

Board Report, of the Bombardier 

DHC–8 Maintenance Program Manual 

PSM 1–8–7, dated February 20, 2012. 

• de Havilland Dash 8 Series 200 

Maintenance Task Card 531X1, Revision 

16, in Section 8, Electrical Wiring 

Interconnection System Inspection 

Program, of Part 1, Maintenance Review 

Board Report, of the Bombardier 

DHC–8 Maintenance Program Manual 

PSM 1–82–7, dated February 20, 2012. 

• de Havilland Dash 8 Series 200 

Maintenance Task Card 631X1, Revision 

16, in Section 8, Electrical Wiring 

Interconnection System Inspection 

Program, of Part 1, Maintenance Review 

Board Report, of the Bombardier 

DHC–8 Maintenance Program Manual 

PSM 1–82–7, dated February 20, 2012. 

• de Havilland Dash 8 Series 300 

Maintenance Task Card 531X1, Revision 

25, in Section 8, Electrical Wiring 

Interconnection System Inspection 

Program, of Part 1, Maintenance Review 

Board Report, of the Bombardier DHC– 

8 Maintenance Program Manual PSM 1– 

83–7, dated February 20, 2012. 

• de Havilland Dash 8 Series 300 

Maintenance Task Card 631X1, Revision 

25, in Section 8, Electrical Wiring 

Interconnection System Inspection 

Program, of Part 1, Maintenance Review 

Board Report, of the Bombardier DHC– 

8 Maintenance Program Manual, PSM 

1–83–7, dated February 20, 2012. 

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. 

This proposed AD requires revisions 

to certain operator maintenance 

documents to include new inspections. 

Compliance with these inspections is 

required by section 91.403(c) of the 

Federal Aviation Regulations (14 CFR 

91.403(c)). For airplances that have been 

previously modified, altered, or repaired 

in the areas addressed by these 

inspections, an operator might not be 

able to accomplish the inspections 

described in the revisions. In this 

situation to comply with 14 CFR 

91.403(c), the operator must request 

approval of an alternative method of 

compliance (AMOC) in accordance with 

the provisions of paragraph (j)(1) of this 

proposed AD. The request should 

include a description of changes to the 

required inspections that will ensure the 

continued damage tolerance of the 

affected structure. 

Costs of Compliance 

Based on the service information, we 

estimate that this proposed AD would 

affect about 89 products of U.S. registry. 


TKELLEY on DSK3SPTVN1PROD with PROPOSALS
Federal Register / Vol. 78, No. 70 / Thursday, April 11, 2013 / Proposed Rules 21575 

We also estimate that it would take 

about 1 work-hour per product to 

comply with the basic requirements of 

this proposed AD. The average labor 

rate is $85 per work-hour. Based on 

these figures, we estimate the cost of the 

proposed AD on U.S. operators to be 

$7,565, or $85 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), 

(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. 

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 adding 

the following new airworthiness 

directive (AD): 

Bombardier, Inc.: Docket No. FAA–2013– 

0298; Directorate Identifier 2012–NM– 

175–AD. 

(a) Comments Due Date 

We must receive comments by May 28, 

2013. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Bombardier, Inc. Model 

DHC–8–102, –103, –106, –201, –202, –301, 

–311, and –315 airplanes, certificated in any 

category, serial numbers 003 and subsequent. 

(d) Subject 

Joint Aircraft System Component (JASC)/ 

Air Transport Association (ATA) of America 

Code 24, Electrical power. 

(e) Reason 

This AD was prompted by reports of dual 

alternating current (AC) generator failure 

during flight. The failure was attributed to 

wire chafing along the wing lower flap 

shroud. We are issuing this AD to prevent 

failure of both AC generators due to wire 

chafing, which could result in loss of power 

to the anti-icing heaters for the elevator horn, 

engine inlet, and propeller, and consequent 

ice accumulation in these areas, which could 

adversely affect the controllability of the 

airplane. 

(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) Maintenance Program Revision 

Within 30 days after the effective date of 

this AD: Revise the airplane maintenance 

program by incorporating de Havilland Dash 

8 Maintenance Task Cards 531X1 and 631X1, 

General visual inspection of the wiring and 

associated electrical wiring interconnection 

system (EWIS), in Section 8, Electrical 

Wiring Inspection Program, of Part 1, 

Maintenance Review Board Report into the 

applicable maintenance program manual 

specified in paragraphs (g)(1), (g)(2), and 

(g)(3) of this AD. 

(1) For Model DHC–8–100 series airplanes: 

Bombardier DHC–8 Maintenance Program 

Manual PSM 1–8–7, Revision 25, dated 

February 20, 2012. 

(2) For Model DHC–8–200 series airplanes: 

Bombardier DHC–8 Maintenance Program 

Manual PSM 1–82–7, Revision 16, dated 

February 20, 2012. 

(3) For Model DHC–8–300 series airplanes: 

Bombardier DHC–8 Maintenance Program 

Manual PSM 1–83–7, Revision 25, dated 

February 20, 2012. 

(h) Initial Task Compliance Time 

The initial compliance time for the tasks 

specified in the maintenance task cards 

specified in paragraph (g) of this AD is at the 

applicable time specified in paragraph (h)(1) 

or (h)(2) of this AD. 

(1) For airplanes with 45,000 total flight 

hours or more as of the effective date of this 

AD: Within 1,000 flight hours after the 

effective date of this AD. 

(2) For airplanes with less than 45,000 total 

flight hours as of the effective date of this 

AD: Within 6,000 flight hours after the 

effective date of this AD, but not to exceed 

46,000 total flight hours. 

(i) No Alternative Actions or Intervals 

After accomplishing the revisions required 

by paragraph (g) of this AD, no alternative 

actions (e.g., inspections) or intervals may be 

used, unless the actions and intervals are 

approved as an alternative method of 

compliance (AMOC) in accordance with the 

procedures specified in paragraph (j)(1) of 

this AD. 

(j) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, New York Aircraft 

Certification Office (ACO), ANE–170, FAA, 

has the authority to approve AMOCs for this 

AD, if requested using the procedures found 

in 14 CFR 39.19. 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 ACO, send it 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. 

(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. 

(k) Related Information 

(1) Refer to MCAI Canadian Airworthiness 

Directive CF–2012–25, dated August 28, 

2012, and the service information specified 

in paragraphs (k)(1)(i) through (k)(1)(vi) of 

this AD, for related information. 


TKELLEY on DSK3SPTVN1PROD with PROPOSALS
21576 Federal Register / Vol. 78, No. 70 / Thursday, April 11, 2013 / Proposed Rules 

(i) de Havilland Dash 8 Series 100 

Maintenance Task Card 531X1, in Section 8, 

Electrical Wiring Interconnection System 

Inspection Program, of Part 1, Maintenance 

Review Board Report, of the Bombardier 

DHC–8 Maintenance Program Manual PSM 

1–8–7, Revision 25, dated February 20, 2012. 

(ii) de Havilland Dash 8 Series 100 

Maintenance Task Card 631X1, in Section 8, 

Electrical Wiring Interconnection System 

Inspection Program, of Part 1, Maintenance 

Review Board Report, of the Bombardier 

DHC–8 Maintenance Program Manual PSM 

1–8–7, Revision 25, dated February 20, 2012. 

(iii) de Havilland Dash 8 Series 200 

Maintenance Task Card 531X1, in Section 8, 

Electrical Wiring Interconnection System 

Inspection Program, of Part 1, Maintenance 

Review Board Report, of the Bombardier 

DHC–8 Maintenance Program Manual PSM 

1–82–7, Revision 16, dated February 20, 

2012. 

(iv) de Havilland Dash 8 Series 200 

Maintenance Task Card 631X1, in Section 8, 

Electrical Wiring Interconnection System 

Inspection Program, of Part 1, Maintenance 

Review Board Report, of the Bombardier 

DHC–8 Maintenance Program Manual PSM 

1–82–7, Revision 16, dated February 20, 

2012. 

(v) de Havilland Dash 8 Series 300 

Maintenance Task Card 531X1, in Section 8, 

Electrical Wiring Interconnection System 

Inspection Program, of Part 1, Maintenance 

Review Board Report, of the Bombardier 

DHC–8 Maintenance Program Manual PSM 1 

83–7, Revision 25, dated February 20, 2012. 

(vi) de Havilland Dash 8 Series 300 

Maintenance Task Card 631X1, in Section 8, 

Electrical Wiring Interconnection System 

Inspection Program, of Part 1, Maintenance 

Review Board Report, of the Bombardier 

DHC–8 Maintenance Program Manual, PSM 

1–83–7, Revision 25, dated February 20, 

2012. 

(2) For service information identified in 

this AD, contact Bombardier, Inc., Q-Series 

Technical Help Desk, 123 Garratt Boulevard, 

Toronto, Ontario M3K 1Y5, Canada; 

telephone 416–375–4000; fax 416–375–4539; 

email thd.qseries@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. 

Issued in Renton, Washington, on March 

28, 2013. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2013–08453 Filed 4–10–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0300; Directorate 

Identifier 2011–NM–163–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 757–200, 

757–200CB, and 757–200PF airplanes. 

This proposed AD was prompted by a 

report that a forward-most cam latch of 

the forward center cam latch pair on a 

main cargo door (MCD) broke during 

flight. This proposed AD would require 

performing repetitive inspections of the 

MCD cam latches; replacing cam 

latches, certain bolts, and door hinge 

fittings; performing related investigative 

and corrective actions, if necessary; and 

MCD rigging. We are proposing this AD 

to detect and correct cracked or 

damaged cam latches, latch pins, and 

latch pin cross bolts, which could 

reduce the structural integrity of the 

MCD, and result in potential rapid 

decompression of the airplane and 

potential loss of the cargo door from the 

airplane. 

DATES: We must receive comments on 

this proposed AD by May 28, 2013. 

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; 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: 

Kimberly DeVoe, 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) 917–6495; 

fax: (425) 917–6590; email: 

kimberly.devoe@faa.gov. 

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– 

2013–0300; Directorate Identifier 2011– 

NM–163–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 received a report that the forwardmost cam latch on the forward center 

cam latch pair on a main cargo door 

(MCD) broke during flight on a Model 

757 airplane. Cracked or damaged cam 

latches, latch pins, and latch pin cross 

bolts, if not corrected, could reduce the 

structural integrity of the MCD, and 

result in potential rapid decompression 

of the airplane and potential loss of the 


TKELLEY on DSK3SPTVN1PROD with PROPOSALS