31762 Federal Register / Vol. 77, No. 104 / Wednesday, May 30, 2012 / Proposed Rules 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 14 CFR part 

39 as follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

1. The authority citation for part 39 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

2. The FAA amends § 39.13 by 

removing airworthiness directive (AD) 

2005–07–20, Amendment 39–14045 (70 

FR 17603, April 7, 2005), and adding 

the following new AD. 

The Boeing Company: Docket No. FAA– 

2010–0856; Directorate Identifier 2010– 

NM–117–AD. 

(a) Comments Due Date 

We must receive comments by July 16, 

2012. 

(b) Affected ADs 

This AD supersedes AD 2005–07–20, 

Amendment 39–14045 (70 FR 17603, April 7, 

2005). 

(c) Applicability 

This AD applies to The Boeing Company 

Model 737–600, –700, –700C, –800, and –900 

series airplanes, delivered with the Rockwell 

Collins Enhanced Digital Flight Control 

System (EDFCS), certificated in any category; 

as identified in the Variable Number table in 

Section 1.A., Effectivity, of Boeing Alert 

Service Bulletin 737–22A1211, dated April 

13, 2010. 

Note 1 to paragraph (c) of this AD: This 

AD is applicable to all airplanes listed in the 

Variable Number table, and is not defined by 

the ‘‘Group 1’’ description in Section 1.A. of 

Boeing Alert Service Bulletin 737–22A1211, 

dated April 13, 2010. 

(d) Subject 

Joint Aircraft System Component (JASC)/ 

Air Transport Association (ATA) of America 

Code 22, Auto Flight. 

(e) Unsafe Condition 

This AD was prompted by reports of 

undetected erroneous output from a single 

radio altimeter channel, which resulted in 

premature autothrottle retard during 

approach. We are issuing this AD to detect 

and correct an unsafe condition associated 

with erroneous output from a radio altimeter 

channel, which could result in premature 

autothrottle landing flare retard and the loss 

of automatic speed control, and consequent 

loss of control of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Retained Actions With No Changes 

This paragraph restates the actions 

required by paragraph (f) of AD 2005–07–20, 

Amendment 39–14045 (70 FR 17603, April 7, 

2005). For airplanes identified in Boeing 

Alert Service Bulletin 737–22A1164, dated 

May 20, 2004: Within 12 months after May 

12, 2005 (the effective date of AD 2005–07– 

20, Amendment 39–14045 (70 FR 17603, 

April 7, 2005)), install and test an updated 

version of the operational program software 

(OPS) of the EDFCS flight control computers 

(FCCs), in accordance with Boeing Alert 

Service Bulletin 737–22A1164, dated May 

20, 2004. 

(h) New Requirements 

Within 3 months after the effective date of 

this AD: Inspect to determine the part 

number of the OPS of the FCCs, in 

accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

737–22A1211, dated April 13, 2010. 

Installing software as required by paragraph 

(h)(1) of this AD, or verifying that the 

software is installed as specified by 

paragraph (h)(2) of this AD, terminates the 

requirements of paragraph (g) of this AD. 

(1) For any OPS having a part number 

identified in table 1 of the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

737–22A1211, dated April 13, 2010: Before 

further flight, install software specified in 

table 2 of Boeing Alert Service Bulletin 737– 

22A1211, dated April 13, 2010, or install 

software that is approved by the Boeing 

Commercial Airplanes Organization 

Designation Authorization (ODA) after April 

13, 2010, that is fully interchangeable with 

the software specified in table 2 of Boeing 

Alert Service Bulletin 737–22A1211, dated 

April 13, 2010. Do the installation in 

accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

737–22A1211, dated April 13, 2010. 

(2) For any OPS having a part number 

identified in table 2 of the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

737–22A1211, dated April 13, 2010: No 

further action is required by this paragraph. 

(i) 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) AMOCs approved previously in 

accordance with AD 2005–07–20, 

Amendment 39–14045 (70 FR 17603, April 7, 

2005), are approved as AMOCs for the 

corresponding provisions of this AD. 

(j) Related Information 

(1) For more information about this AD, 

contact Gregg Nesemeier, Senior Aerospace 

Engineer, Systems and Equipment Branch, 

ANM–130S, FAA, Seattle Aircraft 

Certification Office (ACO), 1601 Lind Avenue 

SW., Renton, Washington 98057–3356; 

phone: (425) 917–6479; fax: (425) 917–6590; 

email: gregg.nesemeier@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 98057–3356. For information on 

the availability of this material at the FAA, 

call 425–227–1221. 

Issued in Renton, Washington, on May 21, 

2012. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2012–13028 Filed 5–29–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0490; Directorate 

Identifier 2012–NM–066–AD] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for all The 

Boeing Company Model 707 airplanes, 

and Model 720 and 720B series 

airplanes. This proposed AD was 

prompted by reports of cracking of the 

midspar fittings, and of the engine and 

nacelle strut separating from the 

airplane. This proposed AD would 

require performing a detailed inspection 

of the midspar fittings of the nacelle 

strut to confirm that the correct part 

number is installed, and installing the 

correct part number if necessary; 

performing repetitive high frequency 

eddy current inspections (HFEC) of the 

midspar fittings of the nacelle strut for 

cracks, and repair if necessary; and 


srobinson on DSK4SPTVN1PROD with PROPOSALS
Federal Register / Vol. 77, No. 104 / Wednesday, May 30, 2012 / Proposed Rules 31763 

performing repetitive general visual 

inspections of the nacelle struts to verify 

that the nacelle strut has not drooped 

below its normal position, applying the 

droop stripe to the nacelle strut and 

sailboat fairing if necessary, and repair 

if necessary. We are proposing this AD 

to detect and correct cracking of the 

midspar fitting, which could result in 

separation of the nacelle strut and 

engine from the airplane while in flight, 

and consequent loss of controllability of 

the airplane. 

DATES: We must receive comments on 

this proposed AD by July 16, 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: 

Berhane Alazar, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office, 

165501 Lind Avenue SW., Renton, WA 

98057–3356; phone: (425) 917–6577; 

fax: (425) 917–6590; email: 

Berhane.Alazar@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– 

2012–0490; Directorate Identifier 2012– 

NM–066–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 fatigue 

cracking of the midspar fittings, and the 

engine and nacelle strut separating from 

the airplane. Operators have reported 

that the cracking occurred on more than 

40 airplanes with approximately 9,900 

to 63,000 flight hours. In addition, there 

has been a report of the engine number 

3 nacelle strut separating from the 

airplane and contacting the engine 

number 4 nacelle strut, which also 

separated from the airplane. This 

condition, if not corrected, could result 

in a fractured midspar fitting, which 

could cause a separation of the nacelle 

strut and engine from the airplane while 

in flight, resulting in loss of 

controllability of the airplane. 

Relevant Service Information 

We reviewed Boeing 707 Alert Service 

Bulletin A3537, dated January 30, 2012. 

That service information describes 

procedures for: 

• Performing a detailed inspection of 

the midspar fittings of the engine 

number 2 and 3 nacelle struts to confirm 

that the correct part number is installed, 

and installing the correct part number if 

necessary. 

• Performing HFEC inspections of the 

midspar fittings of the engine number 2 

and 3 nacelle struts for cracks, and 

repairing if necessary. 

• Performing repetitive general visual 

inspections of the nacelle struts of 

engine numbers 1, 2, 3, and 4 to verify 

that the nacelle strut has not drooped 

below its normal position, applying the 

droop stripe to the nacelle strut and 

sailboat fairing if necessary, and 

repairing if necessary. 

The initial compliance times for the 

HFEC and general visual inspections, 

and the application of the droop stripe 

if necessary, is at the later of: (1) Within 

1,500 flight cycles or 48 months from 

the replacement of the nacelle strut 

inboard and outboard midspar fittings, 

whichever occurs first, or (2) within 120 

days. 

For the HFEC inspection, the 

repetitive interval is within 250 flight 

cycles or 12 months, whichever occurs 

first. 

For the general visual inspection, the 

repetitive interval is 30 flight cycles, 

except after both midspar fittings are 

replaced on the strut, the next 

inspection would be performed within 

1,500 flight cycles or 48 months, 

whichever occurs first, from the 

replacement of both the nacelle strut 

inboard and outboard midspar fittings. 

Boeing 707 Alert Service Bulletin 

A3537, dated January 30, 2012, refers to 

Boeing 707/720 Service Bulletin 3183, 

Revision 5, dated September 16, 1993, 

as an additional source of guidance for 

the HFEC inspections of the midspar 

fittings of the engine number 2 and 3 

nacelle struts for cracks. 

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 the same 

type design. 

Proposed AD Requirements 

This proposed AD would require 

accomplishing the actions specified in 

the service information described 

previously, except as discussed under 

‘‘Differences Between the Proposed AD 

and the Service Information.’’ 

Differences Between the Proposed AD 

and the Service Information 

Boeing 707 Alert Service Bulletin 

A3537, dated January 30, 2012, 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. 


srobinson on DSK4SPTVN1PROD with PROPOSALS
31764 Federal Register / Vol. 77, No. 104 / Wednesday, May 30, 2012 / Proposed Rules 

Boeing 707 Alert Service Bulletin 

A3537, dated January 30, 2012, refers to 

‘‘Manual 707, 720 NDT Part 6, 51–00– 

00 Figure 24 as an accepted procedure’’ 

for the HFEC inspection. This proposed 

AD would require that the inspection 

must be done in accordance with 

Subject 51–00–00 Figure 24, Steel Part 

Surface Inspection (Impedance Plane 

Display), of Part 6, Eddy Current, of the 

Boeing 707, 720 Nondestructive Test 

Manual, Document D6–48023, Revision 

120, dated March 15, 2012. 

Costs of Compliance 

We estimate that this proposed AD 

affects 11 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 

Detailed inspection, repetitive HFEC inspections and repetitive general visual inspections of the midspar fittings of 

the nacelle strut.

23 work-hours × $85 per hour 

= $1,955 

$0 $1,955 $21,505 

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 

Install the correct part number 130 work-hours × $85 per hour = $11,050 $7,867 × 4 = $31,468 ......... $42,518 

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– 

2012–0490; Directorate Identifier 2012– 

NM–066–AD. 

(a) Comments Due Date 

We must receive comments by July 16, 

2012. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to all The Boeing 

Company Model 707–100 long body, –200, 

–100B long body, and –100B short body 

series airplanes; Model 707–300, –300B, 

–300C, and –400 series airplanes; and Model 

720 and 720B series airplanes; certificated in 

any category. 

(d) Subject 

Joint Aircraft System Component (JASC)/ 

Air Transport Association (ATA) of America 

Code 54, Nacelles/Pylons. 

(e) Unsafe Condition 

This AD was prompted by reports of 

cracking of the midspar fittings and of the 

engine and nacelle strut separating from the 

airplane. We are issuing this AD to detect 

and correct cracking of the midspar fitting, 

which could result in separation of the 

nacelle strut and engine from the airplane 

while in flight, and consequent loss of 

controllability of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Detailed Inspection 

Within 120 days after the effective date of 

this AD: Do a detailed inspection of the 

midspar fittings of the engine number 2 and 

3 nacelle struts to confirm that the correct 

part number is installed, in accordance with 

the Accomplishment Instructions of Boeing 

707 Alert Service Bulletin A3537, dated 

January 30, 2012. If any incorrect part 

number is found: Before further flight, install 

the correct part number, in accordance with 

the Accomplishment Instructions of Boeing 


srobinson on DSK4SPTVN1PROD with PROPOSALS
Federal Register / Vol. 77, No. 104 / Wednesday, May 30, 2012 / Proposed Rules 31765 

707 Alert Service Bulletin A3537, dated 

January 30, 2012. 

Note 1 to paragraph (g) of this AD: Boeing 

707 Alert Service Bulletin A3537, dated 

January 30, 2012, refers to Boeing 707/720 

Service Bulletin 3183, Revision 5, dated 

September 16, 1993, as an additional source 

of guidance for high frequency eddy current 

inspections of the midspar fittings of the 

engine number 2 and 3 nacelle struts for 

cracks. 

(h) High Frequency Eddy Current Inspection 

(HFEC) 

At the applicable times specified in 

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

Alert Service Bulletin A3537, dated January 

30, 2012, except as provided in paragraph (j) 

of this AD: Do an HFEC inspection of the 

midspar fittings of the engine number 2 and 

3 nacelle struts for cracks, in accordance with 

the Accomplishment Instructions of Boeing 

707 Alert Service Bulletin A3537, dated 

January 30, 2012, except as provided by 

paragraph (k) of this AD. If any crack is 

found, before further flight, repair using a 

method approved in accordance with the 

procedures specified in paragraph (m) of this 

AD. Thereafter, repeat the inspection at the 

applicable intervals specified in paragraph 

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

Service Bulletin A3537, dated January 30, 

2012. 

(i) General Visual Inspection of the Nacelle 

Struts of Engine Numbers 1, 2, 3, and 4 

At the applicable times in paragraph 1.E., 

‘‘Compliance,’’ of Boeing 707 Alert Service 

Bulletin A3537, dated January 30, 2012, 

except as provided in paragraph (j) of this 

AD: Do a general visual inspection of the 

nacelle struts of engine numbers 1, 2, 3, and 

4 to verify that the nacelle strut has not 

drooped below its normal position, in 

accordance with the Accomplishment 

Instructions of Boeing 707 Alert Service 

Bulletin A3537, dated January 30, 2012. 

Thereafter, repeat the inspection at the 

applicable intervals specified in paragraph 

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

Service Bulletin A3537, dated January 30, 

2012. 

(1) If any nacelle strut has drooped below 

its normal position: Before further flight, 

repair using a method approved in 

accordance with the procedures specified in 

paragraph (m) of this AD. 

(2) If any nacelle strut has not drooped 

below its normal position, and no droop 

stripe has been applied, as specified in 

Boeing 707/720 Service Bulletin 3377, dated 

November 21, 1979: At the applicable times 

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

707 Alert Service Bulletin A3537, dated 

January 30, 2012, except as provided in 

paragraph (j) of this AD: Apply the droop 

stripe to the nacelle strut and sailboat fairing, 

on each side of the engine numbers 1, 2, 3, 

and 4 nacelle struts, in accordance with the 

Accomplishment Instructions of Boeing 707 

Alert Service Bulletin A3537, dated January 

30, 2012. 

(j) Exception to the Compliance Time 

Where Boeing 707 Alert Service Bulletin 

A3537, dated January 30, 2012, specifies a 

compliance time based on ‘‘the original issue 

date of this service bulletin,’’ this AD 

requires compliance within the specified 

compliance time after the effective date of 

this AD. 

(k) Exception to the Service Information 

Where Boeing 707 Alert Service Bulletin 

A3537, dated January 30, 2012, refers to 

‘‘Manual 707, 720 NDT Part 6, 51–00–00 

Figure 24 as an accepted procedure’’ for the 

HFEC inspection, this AD requires that the 

inspection must be done in accordance with 

Subject 51–00–00 Figure 24, Steel Part 

Surface Inspection (Impedance Plane 

Display), of Part 6, Eddy Current, of the 

Boeing 707, 720 Nondestructive Test Manual, 

Document D6–48023, Revision 120, dated 

March 15, 2012. 

(l) Credit for Previous Actions 

This paragraph provides credit for the 

installation of the engine droop lines 

required by paragraph (i) of this AD, if those 

actions were performed before the effective 

date of this AD using Boeing 707/720 Service 

Bulletin 3377, dated November 21, 1979. 

(m) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle Aircraft 

Certification Office (ACO), ANM–120S, 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, ANM–120S 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 Berhane Alazar, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

phone: (425) 917–6577; fax: (425) 917–6590; 

email: Berhane.Alazar@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. 

Issued in Renton, Washington, on May 21, 

2012. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2012–13039 Filed 5–29–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF COMMERCE 

Minority Business Development 

Agency 

15 CFR Part 1400 

[Docket No. 120517080–2080–01] 

Petition for Inclusion of the ArabAmerican Community in the Groups 

Eligible for MBDA Services 

AGENCY: Minority Business 

Development Agency, Commerce. 

ACTION: Notice of proposed rulemaking 

and request for comments. 

SUMMARY: The Minority Business 

Development Agency (MBDA) publishes 

this notice regarding the petition 

received on January 11, 2012 from the 

American-Arab Anti-Discrimination 

Committee (ADC) requesting formal 

designation of Arab-Americans as a 

minority group that is socially or 

economically disadvantaged pursuant to 

15 CFR art 1400. The formal designation 

of the Arab-American community as a 

group that is socially or economically 

disadvantaged would allow the 

members of this community to receive 

assistance from MBDA funded 

programs, such as the MBDA Business 

Center program. The ADC filed a 

petition, pursuant to 15 CFR part 

1400.3, including information 

specifically related to social and 

economic discrimination against ArabAmericans. This Notice provides public 

notice that the United States 

Department of Commerce (Department) 

will consider the petition and requests 

public comment on the propriety of this 

designation. MBDA will make a 

decision on the application no later than 

June 27, 2012. 

DATES: Comments must be received by 

MBDA no later than June 29, 2012. 

ADDRESSES: You may submit comments, 

identified with Docket No. 120517080– 

2080–01, using any of the following 

methods: 

• Mail, Hand/Delivery/Courier: Ms. 

Josephine Arnold, Chief Counsel, 


srobinson on DSK4SPTVN1PROD with PROPOSALS