18922 Federal Register / Vol. 78, No. 60 / Thursday, March 28, 2013 / Proposed Rules 

Issued in Burlington, Massachusetts, 

on March 20, 2013. 

Robert J. Ganley, 

Acting Manager, Engine & Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–07210 Filed 3–27–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0215; Directorate 

Identifier 2012–NM–132–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 707–300, 

707–300B, and 707–300C series 

airplanes; and certain Model 727C, 727– 

100C, and 727–200F series airplanes. 

This proposed AD was prompted by a 

report that a cam latch on the 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 rapid decompression 

of the airplane and potential loss of the 

MCD during flight. 

DATES: We must receive comments on 

this proposed AD by May 13, 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, WA 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, WA. 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 A. DeVoe, Aerospace 

Engineer, Cabin Safety and 

Environmental Systems Branch, ANM– 

150S, FAA, 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– 

2013–0215; Directorate Identifier 2012– 

NM–132–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 (cam latch number 3) on 

the MCD broke during flight on a Model 

757 airplane. That airplane had 

accumulated 20,000 total flight hours 

and 9,500 total flight cycles when the 

cam latch broke. 

Certain Model 707–300, 707–300B, 

and 707–300C series airplanes; and 

certain Model 727C, 727–100C, and 

727–200F series airplanes; have an MCD 

with a similar design to the MCD on the 

Model 757 airplane. Therefore, those 

Model 707–300, 707–300B, and 707– 

300C series airplanes; and Model 727C, 

727–100C, and 727–200F series 

airplanes; might be subject to the unsafe 

condition revealed on Model 757 

airplanes. 

The MCD is an outward-hinging door 

that requires a locking mechanism to 

keep the door closed. The latch pins in 

the lower sill of the MCD interlock with 

the cam latches installed in the bottom 

of the MCD. When a latch pin interlocks 

with a cam latch, the cam latch rotates 

into the closed position and holds the 

door closed. 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 rapid decompression 

of the airplane and potential loss of the 

MCD during flight. 

Relevant Service Information 

We reviewed Boeing 707 Alert Service 

Bulletin A3536, dated February 6, 2012 

(for Model 707–300, 707–300B, and 

707–300C series airplanes); and Boeing 

Alert Service Bulletin 727–52A0150, 

dated January 30, 2012 (for Model 727C, 

727–100C, and 727–200F series 

airplanes). For information on the 

procedures and compliance times, see 

this service information at http:// 

www.regulations.gov by searching for 

Docket No. FAA–2013–0215. 

Concurrent Service Information 

Boeing 707 Alert Service Bulletin 

A3536, dated February 6, 2012 (for 

Model 707–300, 707–300B, and 707– 

300C series airplanes), specifies 

concurrent or prior accomplishment of 

Boeing 707/720 Service Bulletin 3477, 

Revision 2, dated April 15, 1993 (for 

Model 707–300, 707–300B, and 707– 

300C series airplanes). Boeing Alert 

Service Bulletin 727–52A0150, dated 

January 30, 2012 (for Model 727C, 727– 

100C, and 727–200F series airplanes), 

specifies concurrent or prior 

accomplishment of Boeing Service 

Bulletin 727–52–0142, Revision 2, dated 

April 15, 1993 (for Model 727–100C and 

727–200F series airplanes). For 

information on the procedures, see this 

service information at http:// 

mstockstill on DSK4VPTVN1PROD with PROPOSALS

Federal Register / Vol. 78, No. 60 / Thursday, March 28, 2013 / Proposed Rules 18923 

www.regulations.gov by searching for 

Docket No. FAA–2013–0215. 

Other Relevant Rulemaking 

On October 7, 1991, the FAA issued 

AD 91–22–04, Amendment 39–8064 (56 

FR 55223, October 25, 1991), for Model 

707/720, 727–100C, and 727–200F 

series airplanes. That AD requires the 

use of certain special operating 

procedures for the MCD, and the 

inspection, necessary repair, and 

eventual replacement of MCD cam 

latches, cam latch bellcranks, and 

pressure relief door hinge fittings in 

accordance with the Accomplishment 

Instructions of Boeing Service Bulletin 

3477, dated July 26, 1990 (for Model 

707/720 series airplanes); or Boeing 

Service Bulletin 727–52–0142, dated 

July 26, 1990 (for Model 727 series 

airplanes). For this proposed AD, those 

actions must be accomplished 

concurrently with the Accomplishment 

Instructions of Boeing 707/720 Service 

Bulletin 3477, Revision 2, dated April 

15, 1993 (for Model 707–300, 707–300B, 

and 707–300C series airplanes); or 

Boeing Service Bulletin 727–52–0142, 

Revision 2, dated April 15, 1993 (for 

Model 727–100C and 727–200F series 

airplanes). 

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 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 

Although Boeing 707 Alert Service 

Bulletin A3536, dated February 6, 2012 

(for Model 707–300, 707–300B, and 

707–300C series airplanes); and Boeing 

Alert Service Bulletin 727–52A0150, 

dated January 30, 2012 (for Model 727C, 

727–100C, and 727–200F series 

airplanes); specify that operators may 

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 18 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/Torque/Measurement .......... 3 work-hours × $85 per hour = $255 .. $0 .......................... $255 ...................... $4,590. 

MCD Modification ................................. 48 work-hours × $85 per hour = 

$4,080.

Up to $8,821 1 ...... Up to $12,901 ....... Up to $232,218. 

1Special tooling is available from the airplane manufacturer; $8,821 is the purchase price and $180 per day is the rental rate. 

We estimate the following costs to do 

any necessary replacements that would 

be required based on the results of the 

proposed inspections. We have no way 

of determining the number of aircraft 

that might need these replacements: 

ON-CONDITION COSTS

Action Labor cost Parts 

cost Cost per product 

Replace Cross Bolts .................................................. 3 work-hours × $85 per hour = $255 ........................ $0 $255. 

Replace Cam Latch/Latch Pin ................................... 1 work-hour × $85 per hour = $85 ............................ 0 $85 per latch/pin. 

Repetitive Inspections ............................................... 3 work-hours × $85 = $255 per inspection cycle ...... 0 $255 per inspection cycle. 

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 

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18924 Federal Register / Vol. 78, No. 60 / Thursday, March 28, 2013 / Proposed Rules 

(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– 

2013–0215; Directorate Identifier 2012– 

NM–132–AD. 

(a) Comments Due Date 

We must receive comments by May 13, 

2013. 

(b) Affected ADs 

None. 

(c) Applicability 

The Boeing Company airplanes, 

certificated in any category, as identified in 

paragraphs (c)(1) and (c)(2) of this AD. 

(1) Model 707–300, 707–300B, and 707– 

300C series airplanes, as identified in Boeing 

707 Alert Service Bulletin A3536, dated 

February 6, 2012. 

(2) Model 727C, 727–100C, and 727–200F 

series airplanes, as identified in Boeing Alert 

Service Bulletin 727–52A0150, dated January 

30, 2012. 

(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 

cam latch on the main cargo door (MCD) 

broke during flight. We are issuing this AD 

to detect and correct cracked or damaged cam 

latches, latch pins, and latch pin cross bolts, 

which could affect the structural integrity of 

the MCD, and result in rapid decompression 

of the airplane and potential loss of the MCD 

during flight. 

(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 

707 Alert Service Bulletin A3536, dated 

February 6, 2012 (for Model 707–300, 707– 

300B, and 707–300C series airplanes); or 

Boeing Alert Service Bulletin 727–52A0150, 

dated January 30, 2012 (for Model 727C, 727– 

100C, and 727–200F series airplanes); except 

as provided by paragraph (k)(1) of this AD: 

Do a detailed inspection of the MCD 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 bolts; rig the MCD, as 

applicable; and do all applicable related 

investigative and corrective actions, except as 

required by paragraph (k)(2) of this AD; in 

accordance with the Accomplishment 

Instructions of Boeing 707 Alert Service 

Bulletin A3536, dated February 6, 2012 (for 

Model 707–300, 707–300B, and 707–300C 

series airplanes); or Boeing Alert Service 

Bulletin 727–52A0150, dated January 30, 

2012 (for Model 727C, 727–100C, and 727– 

200F series airplanes). Do all applicable 

related investigative and corrective actions at 

the applicable time specified in paragraph 

1.E., ‘‘Compliance,’’ of Boeing 707 Alert 

Service Bulletin A3536, dated February 6, 

2012 (for Model 707–300, 707–300B, and 

707–300C series airplanes); or Boeing Alert 

Service Bulletin 727–52A0150, dated January 

30, 2012 (for Model 727C, 727–100C, and 

727–200F series airplanes). 

(h) Repetitive Inspections 

Repeat the applicable inspections specified 

in paragraph (g) of this AD, as identified 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 

707 Alert Service Bulletin A3536, dated 

February 6, 2012 (for Model 707–300, 707– 

300B, and 707–300C series airplanes); or 

Boeing Alert Service Bulletin 727–52A0150, 

dated January 30, 2012 (for Model 727C, 727– 

100C, and 727–200F series airplanes). The 

Inspection Conditions are defined in Boeing 

707 Alert Service Bulletin A3536, dated 

February 6, 2012 (for Model 707–300, 707– 

300B, and 707–300C series airplanes); and 

Boeing Alert Service Bulletin 727–52A0150, 

dated January 30, 2012 (for Model 727C, 727– 

100C, and 727–200F series airplanes). 

(1) For airplanes found with Inspection 

Condition 2 or 4.2: Repeat the detailed 

inspection of the cam latches and cam pins 

for damage, distress, and incorrect rigging. 

(2) For airplanes found with Inspection 

Condition 4.1: Repeat the general visual 

inspection of the cam latch for broken, 

cracked, missing, or migrated parts. 

(3) For airplanes found with Inspection 

Condition 5: Do the actions specified in 

paragraphs (h)(3)(i), (h)(3)(ii), and (h)(3)(iii) 

of this AD. 

(i) Repeat the general visual inspection of 

the cam latch for broken, cracked, missing, or 

migrated parts. 

(ii) Repeat the detailed inspection of the 

cam latches and cam pins for damage, 

distress, or incorrect rigging. 

(iii) Repeat the high frequency eddy 

current (HFEC) or magnetic particle 

inspection of cam latch 1 and cam latch 2 for 

cracking. 

(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 

707 Alert Service Bulletin A3536, dated 

February 6, 2012 (for Model 707–300, 707– 

300B, and 707–300C series airplanes); or 

Boeing Alert Service Bulletin 727–52A0150, 

dated January 30, 2012 (for Model 727C, 727– 

100C, and 727–200F series airplanes); except 

as provided by paragraph (k)(1) of this AD: 

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 (k)(2) of this AD; in accordance 

with the Accomplishment Instructions of 

Boeing 707 Alert Service Bulletin A3536, 

dated February 6, 2012 (for Model 707–300, 

707–300B, and 707–300C series airplanes); or 

Boeing Alert Service Bulletin 727–52A0150, 

dated January 30, 2012 (for Model 727C, 727– 

100C, and 727–200F series airplanes). Do all 

applicable related investigative and 

corrective actions at the applicable time 

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

Boeing 707 Alert Service Bulletin A3536, 

dated February 6, 2012 (for Model 707–300, 

707–300B, and 707–300C series airplanes); or 

Boeing Alert Service Bulletin 727–52A0150, 

dated January 30, 2012 (for Model 727C, 727– 

100C, and 727–200F series airplanes). 

(j) MCD Post-Rigging Repetitive Inspections 

Repeat the applicable inspections specified 

in paragraph (i) of this AD, as identified in 

paragraph (j)(1) or (j)(2) of this AD, at the 

applicable times specified in table 2 of 

paragraph 1.E., ‘‘Compliance,’’ of Boeing 707 

Alert Service Bulletin A3536, dated February 

6, 2012 (for Model 707–300, 707–300B, and 

707–300C series airplanes); or Boeing Alert 

Service Bulletin 727–52A0150, dated January 

30, 2012 (for Model 727C, 727–100C, and 727 

–200F series airplanes). The Inspection 

Conditions are defined in Boeing 707 Alert 

Service Bulletin A3536, dated February 6, 

2012 (for Model 707–300, 707–300B, and 

707–300C series airplanes); and Boeing Alert 

Service Bulletin 727–52A0150, dated January 

30, 2012 (for Model 727C, 727–100C, and 

727–200F series airplanes). 

(1) For airplanes that have completed the 

MCD rigging: Do the actions specified in 

paragraphs (j)(1)(i), (j)(1)(ii), and (j)(1)(iii) of 

this AD. 

(i) Repeat the general visual inspection of 

the cam latches and latch pins for 

discrepancies. 

(ii) Repeat the detailed inspection of the 

cam latches and latch pins for discrepancies. 

(iii) Repeat the HFEC or magnetic particle 

inspection of cam latch 1 and cam latch 2 for 

cracking. 

(2) For airplanes found with Inspection 

Condition 2: Do the actions specified in 

paragraphs (j)(2)(i) and (j)(2)(ii) of this AD. 

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Federal Register / Vol. 78, No. 60 / Thursday, March 28, 2013 / Proposed Rules 18925 

(i) Repeat the detailed inspection of the 

cam latches and latch pins for damage, 

distress, or incorrect rigging. 

(ii) Repeat the HFEC or magnetic particle 

inspection of cam latch 1 and cam latch 2 for 

cracking. 

(k) Exceptions to Service Bulletin 

Specifications 

The following exceptions apply to this AD. 

(1) Where Boeing 707 Alert Service 

Bulletin A3536, dated February 6, 2012 (for 

Model 707–300, 707–300B, and 707–300C 

series airplanes); or Boeing Alert Service 

Bulletin 727–52A0150, dated January 30, 

2012 (for Model 727C, 727–100C, and 727– 

200F series airplanes); specifies a compliance 

time relative to the issue date of that service 

bulletin, this AD requires compliance within 

the specified compliance time after the 

effective date of this AD. 

(2) Where Boeing 707 Alert Service 

Bulletin A3536, dated February 6, 2012 (for 

Model 707–300, 707–300B, and 707–300C 

series airplanes); or Boeing Alert Service 

Bulletin 727–52A0150, dated January 30, 

2012 (for Model 727C, 727–100C, and 727– 

200F series airplanes); specifies to contact 

Boeing for appropriate action: At the 

applicable time specified in paragraph 1.E., 

‘‘Compliance,’’ of Boeing 707 Alert Service 

Bulletin A3536, dated February 6, 2012 (for 

Model 707–300, 707–300B, and 707–300C 

series airplanes); or Boeing Alert Service 

Bulletin 727–52A0150, dated January 30, 

2012 (for Model 727C, 727–100C, and 727– 

200F series airplanes); repair 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. 

(l) Concurrent Actions 

(1) For airplanes identified in Boeing 707 

Alert Service Bulletin A3536, dated February 

6, 2012: Before or concurrently with 

accomplishment of the detailed inspection 

specified in paragraph (g) of this AD, do a 

general visual inspection of the hinge fittings 

and the cam latches on the MCD, and 

perform related investigative and corrective 

actions as applicable, in accordance with the 

Accomplishment Instructions of Boeing 707/ 

720 Service Bulletin 3477, Revision 2, dated 

April 15, 1993. 

(2) For airplanes identified in Boeing Alert 

Service Bulletin 727–52A0150, dated January 

30, 2012: Before or concurrently with 

accomplishment of the detailed inspection 

specified in paragraph (g) of this AD, do a 

general visual inspection of the hinge fittings 

and the cam latches on the MCD, and 

perform related investigative and corrective 

actions if applicable, in accordance with the 

Accomplishment Instructions of Boeing 

Service Bulletin 727–52–0142, Revision 2, 

dated April 15, 1993. 

(m) Optional Terminating Action 

Accomplishment of the latch mechanism 

adjustment test and the MCD rigging, in 

accordance with the Accomplishment 

Instructions of Boeing 707 Alert Service 

Bulletin A3536, dated February 6, 2012 (for 

Model 707–300, 707–300B, and 707–300C 

series airplanes); or Boeing Alert Service 

Bulletin 727–52A0150, dated January 30, 

2012 (for Model 727C, 727–100C, and 727– 

200F series airplanes); terminates the 

repetitive inspections specified in paragraph 

(h) of this AD. Thereafter, do the MCD postrigging initial inspections and applicable 

related investigative and corrective actions 

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

repetitive inspections specified in paragraph 

(j) of this AD. 

(n) 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. 

(o) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle 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. 

(p) Related Information 

(1) For more information about this AD, 

contact Kimberly A. DeVoe, Aerospace 

Engineer, Cabin Safety and Environmental 

Systems Branch, ANM–150S, FAA, 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, WA 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, 

WA. For information on the availability of 

this material at the FAA, call 425–227–1221. 

Issued in Renton, Washington, on March 

21, 2013. 

Jeffrey E. Duven, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–07213 Filed 3–27–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0212; Directorate 

Identifier 2012–NM–116–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for all 

Airbus Model A330–223F, –223, –321, 

–322, and –323 airplanes. This proposed 

AD was prompted by fatigue load 

analysis that determined that the 

inspection interval for certain pylon 

bolts must be reduced. This proposed 

AD would require a torque check of 

forward engine mount bolts, and 

replacement if necessary. We are 

proposing this AD to detect and correct 

loose or broken bolts, which could lead 

to engine detachment in-flight, and 

damage to the airplane. 

DATES: We must receive comments on 

this proposed AD by May 13, 2013. 

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 Airbus service information 

identified in this proposed AD, contact 

Airbus SAS—Airworthiness Office— 

EAL, 1 Rond Point Maurice Bellonte, 

31707 Blagnac Cedex, France; telephone 

+33 5 61 93 36 96; fax +33 5 61 93 45 

80; email airworthiness.A330- 

A340@airbus.com; Internet http:// 

www.airbus.com. You may review 

copies of the referenced service 

information at the FAA, Transport 

Airplane Directorate, 1601 Lind Avenue 

SW., Renton, WA. For information on 

the availability of this material at the 

FAA, call 425–227–1221. 

mstockstill on DSK4VPTVN1PROD with PROPOSALS