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
Federal Register / Vol. 78, No. 70 / Thursday, April 11, 2013 / Proposed Rules 21577 

cargo door from the airplane. Two of the 

eight cam latches or latch pins being 

broken in close proximity will cause 

loss of the cargo door during flight. 

Relevant Service Information 

We reviewed Boeing Alert Service 

Bulletin 757–52A0091, dated March 9, 

2010. For information on the procedures 

and compliance times, see this service 

information at http:// 

www.regulations.gov by searching for 

Docket No. FAA–2013–0300. 

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 identified 

previously under ‘‘Relevant Service 

Information,’’ except as discussed under 

‘‘Differences Between the Proposed AD 

and the Service Information.’’ 

The phrase ‘‘related investigative 

actions’’ might be used in this proposed 

AD. ‘‘Related investigative actions’’ are 

follow-on actions that (1) are related to 

the primary actions, and (2) are actions 

that further investigate the nature of any 

condition found. Related investigative 

actions in an AD could include, for 

example, inspections. 

In addition, the phrase ‘‘corrective 

actions’’ might be used in this proposed 

AD. ‘‘Corrective actions’’ are actions 

that correct or address any condition 

found. Corrective actions in an AD 

could include, for example, repairs. 

Differences Between the Proposed AD 

and the Service Information 

The Accomplishment Instructions of 

Boeing Alert Service Bulletin 757– 

52A0091, dated March 9, 2010, specify 

to contact the manufacturer for 

disposition of certain repair conditions, 

this proposed AD would require 

operators to repair those conditions 

using a method approved by the FAA. 

Costs of Compliance 

We estimate that this proposed AD 

affects 9 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 

Inspections/Modification .......... 55 work-hours × $85 per hour = $4,675 ................................. None ............ $4,675 $42,075 

Replace cross bolts ................. 3 work-hours × $85 per hour = $255 ...................................... $0 ................. 255 2,295 

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. 

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– 

2013–0300; Directorate Identifier 2011– 

NM–163–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 757–200, 757–200CB, and 757–200PF 

airplanes; certified in any category; as 

identified in Boeing Alert Service Bulletin 

757–52A0091, dated March 9, 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 a report that a 

forward most cam latch on the forward center 

cam latch pair on a main cargo door (MCD) 

broke during flight. We are issuing 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. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) MCD Inspections, Bolt Torque, Latch Pin 

Measurement, Bolt Replacement, and 

Rigging 

At the applicable times specified in table 

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

Alert Service Bulletin 757–52A0091, dated 

March 9, 2010, except as specified in 


TKELLEY on DSK3SPTVN1PROD with PROPOSALS
21578 Federal Register / Vol. 78, No. 70 / Thursday, April 11, 2013 / Proposed Rules 

paragraph (l)(2) of this AD: Do a detailed 

inspection of the cam latches and latch pins 

to detect damage, distress, and incorrect 

rigging; torque the cross bolts; measure the 

extension of the latch pins; replace all alloy 

steel bolts used as latch pin cross bolts with 

corrosion resistant steel (CRES) bolts; rig the 

MCD, as applicable; and do all applicable 

related investigative and corrective actions, 

in accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

757–52A0091, dated March 9, 2010, except 

as required by paragraph (l)(2) of this AD. Do 

all applicable related investigative and 

corrective actions at the applicable time 

specified in paragraph 1.E., ‘‘Compliance’’ of 

Boeing Alert Service Bulletin 757–52A0091, 

dated March 9, 2010. 

(h) Repetitive Inspections 

Repeat the applicable inspections specified 

in paragraph (g) of this AD, as specified in 

paragraphs (h)(1), (h)(2), and (h)(3) of this 

AD, at the applicable times specified in table 

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

Alert Service Bulletin 757–52A0091, dated 

March 9, 2010. The inspection conditions are 

defined in Boeing Alert Service Bulletin 757– 

52A0091, dated March 9, 2010. 

(1) For airplanes found with Inspection 

Condition 5: Repeat the general visual 

inspection for broken, cracked, missing, or 

migrated parts of the cam latches and latch 

pins. 

(2) For airplanes found with Inspection 

Condition 2, 4.2, or 5: Repeat the detailed 

inspection for damage, distress, and incorrect 

rigging of the cam latches and latch pins. 

(3) For airplanes found with Inspection 

Condition 5: Repeat the high frequency eddy 

current or magnetic particle inspection to 

detect signs of cracking of cam latches 1 and 

2. 

(i) MCD Post-Rigging Initial Inspections and 

Related Investigative and Corrective Actions 

At the applicable times specified in table 

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

Alert Service Bulletin 757–52A0091, dated 

March 9, 2010: Do a general visual inspection 

of the cam latches and latch pins for 

discrepancies; a detailed inspection of the 

cam latches and latch pins for discrepancies; 

and an HFEC or magnetic particle inspection 

of cam latch 1 and cam latch 2 for cracking; 

and do all applicable related investigative 

and corrective actions, except as required by 

paragraph (l)(2) of this AD; in accordance 

with the Accomplishment Instructions of 

Boeing Alert Service Bulletin 757–52A0091, 

dated March 9, 2010. Do all applicable 

related investigative and corrective actions at 

the applicable time specified in paragraph 

1.E., ‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 757–52A0091, dated March 9, 2010. 

(j) MCD Post-Rigging Repetitive Inspections 

(1) For all airplanes: Repeat the inspections 

specified in paragraph (i) of this AD, at the 

applicable times specified in table 2 of 

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

Alert Service Bulletin 757–52A0091, dated 

March 9, 2010. 

(2) For airplanes found with Inspection 

Condition 2 as defined in Boeing Alert 

Service Bulletin 757–52A0091, dated March 

9, 2010: Repeat the detailed inspection for 

damage, distress, and incorrect rigging of the 

cam latches and latch pins specified in 

paragraph (i) of this AD on remaining cam 

latches and cam pins at the applicable times 

specified in table 2 of paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 757–52A0091, dated March 9, 2010. 

(k) Parts Installation Prohibition 

As of the effective date of this AD, no 

person may install an alloy steel bolt as a 

cross bolt through any latch pin fitting 

assembly in the lower sill of the MCD on any 

airplane. 

(l) Exceptions to Service Bulletin 

Specifications 

The following exceptions apply in this AD. 

(1) Where Boeing Alert Service Bulletin 

757–52A0091, dated March 9, 2010, specifies 

a compliance time after the date of that 

service bulletin, this AD requires compliance 

within the specified compliance time after 

the effective date of this AD. 

(2) Where Boeing Alert Service Bulletin 

757–52A0091, dated March 9, 2010, specifies 

to contact Boeing for appropriate action: 

Before further flight, repair the discrepancy 

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. 

(m) 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. 

(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. 

(n) Related Information 

(1) For more information about this AD, 

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. 

(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 

28, 2013. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2013–08450 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–2013–0195; Directorate 

Identifier 2013–NE–08–AD] 

RIN 2120–AA64 

Airworthiness Directives; General 

Electric Company Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for all 

General Electric Company (GE) model 

GEnx-2B67 and GEnx-2B67B turbofan 

engines with booster anti-ice (BAI) air 

duct, part number (P/N) 2469M32G01, 

and support bracket, P/N 2469M46G01, 

installed. This proposed AD was 

prompted by reports of cracks in the 

BAI air duct. This proposed AD would 

require initial and repetitive visual 

inspections of the BAI air duct, removal 

from service of the BAI air duct if it fails 

inspection and, as a mandatory 

terminating action, the installation of 

new BAI air duct support brackets. We 

are proposing this AD to prevent failure 

of the BAI air duct, resulting in an inflight shutdown of one or more engines, 

loss of thrust control, and damage to the 

aircraft. 

DATES: We must receive comments on 

this proposed AD by June 10, 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, 


TKELLEY on DSK3SPTVN1PROD with PROPOSALS