6154 Federal Register / Vol. 75, No. 25 / Monday, February 8, 2010 / Proposed Rules 

Dated: January 31, 2010. 

Edward J. DeMarco, 

Acting Director, Federal Housing Finance 

Agency. 

[FR Doc. 2010–2677 Filed 2–5–10; 8:45 am] 

BILLING CODE P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0033; Directorate 

Identifier 2009–NM–099–AD] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Model 767 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: The FAA proposes to 

supersede an existing airworthiness 

directive (AD) that applies to all Model 

767 airplanes. The existing AD currently 

requires repetitive detailed and high 

frequency eddy current (HFEC) 

inspections of the station (STA) 1809.5 

bulkhead for cracking, and corrective 

actions if necessary. This proposed AD 

would expand the inspection area to 

include the vertical inner chord at STA 

1809.5. This proposed AD results from 

reported fatigue cracking in the vertical 

inner chord and the forward outer chord 

while doing the detailed inspection of 

the horizontal inner chord at STA 

1809.5. We are proposing this AD to 

detect and correct fatigue cracking in 

the bulkhead structure at STA 1809.5 

and the vertical inner chord at STA 

1809.5, which could result in failure of 

the bulkhead structure for carrying the 

flight loads of the horizontal stabilizer, 

and consequent loss of controllability of 

the airplane. 

DATES: We must receive comments on 

this proposed AD by March 25, 2010. 

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 20590, 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; e-mail 

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 or 425–227–1152. 

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 

(telephone 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, Airframe Branch, 

ANM–120S, FAA, Seattle Aircraft 

Certification Office, 1601 Lind Avenue, 

SW., Renton, Washington 98057–3356; 

telephone (425) 917–6577; fax (425) 

917–6590. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2010–0033; Directorate Identifier 

2009–NM–099–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 

On November 9, 2006, we issued AD 

2006–24–04, Amendment 39–14833 (71 

FR 68432, November 27, 2006), for all 

Model 767 airplanes. That AD requires 

repetitive detailed and high frequency 

eddy current (HFEC) inspections of the 

station (STA) 1809.5 bulkhead for 

cracking, and corrective actions if 

necessary. That AD resulted from 

fatigue cracks found in the forward 

outer chord and horizontal inner chord 

at STA 1809.5. We issued that AD to 

detect and correct cracking in the 

bulkhead structure at STA 1809.5, 

which could result in failure of the 

bulkhead structure for carrying the 

flight loads of the horizontal stabilizer, 

and consequent loss of controllability of 

the airplane. 

Actions Since Existing AD Was Issued 

Since we issued AD 2006–24–04, an 

operator reported fatigue cracking in the 

vertical inner chord found while doing 

the detailed inspection of the horizontal 

inner chord required by that AD. A 

surface HFEC inspection was done to 

confirm the crack. The crack was found 

on the right side of the structure at a 

fastener hole near buttock line (BL) 28.5, 

water line (WL) 257, common to both 

the horizontal and vertical inner chord. 

The vertical inner chord crack was 

found on an airplane with 28,234 total 

flight cycles. 

Relevant Service Information 

AD 2006–24–04 refers to Boeing Alert 

Service Bulletin 767–53A0131, dated 

March 30, 2006, as the appropriate 

source of service information for the 

required actions. We have reviewed 

Boeing Alert Service Bulletin 767– 

53A0131, Revision 1, dated March 12, 

2009. Revision 1 adds a surface HFEC 

inspection for the vertical inner chord, 

and clarifies the procedures for 

inspecting the horizontal inner chord. 

The service bulletin specifies a 

compliance time of before 15,000 total 

flight cycles or within 6,000 flight 

cycles after the previous PARTS 1–4 

inspection, whichever occurs first, for 

the surface HFEC inspection for the 

vertical inner chord. The service 

bulletin also specifies a repeat interval 

6,000 flight cycles thereafter for the 

surface HFEC inspection for the vertical 

inner chord. 

FAA’s Determination and Requirements 

of the Proposed AD 

We have evaluated all pertinent 

information and identified an unsafe 

condition that is likely to develop on 

other airplanes of the same type design. 

For this reason, we are proposing this 

AD, which would supersede AD 2006– 

WReier-Aviles on DSKGBLS3C1PROD with PROPOSALS

Federal Register / Vol. 75, No. 25 / Monday, February 8, 2010 / Proposed Rules 6155 

24–04 and retain the requirements of the 

existing AD. This proposed AD would 

also require accomplishing the new 

actions specified in the revised service 

bulletin described previously. 

Change to Paragraph (i) of the Existing 

AD 

We have revised paragraph (i) of the 

existing AD to clarify that the 

modification of a forward outer chord 

may be done in accordance with Steps 

4.A through 4.C and 4.G through 4.P of 

Repair 9, dated April 15, 2006, of 

Chapter 53–80–08 of the Boeing 767– 

200 Structural Repair Manual (SRM), 

Document D634T201; Boeing 767–300 

SRM, Document D634T210; Boeing 

767–300F SRM, Document D634T215; 

or Boeing 767–400 SRM, Document 

D634T225; as applicable. For a 

horizontal inner chord, modification 

may be done in accordance with Steps 

4.A, 4.B, and 4.F through 4.P of Repair 

10, dated April 15, 2006, of Chapter 53– 

80–08 of the Boeing 767–200 SRM, 

Document D634T201; Boeing 767–300 

SRM, Document D634T210; Boeing 

767–300F SRM, Document D634T215; 

or Boeing 767–400 SRM, Document 

D634T225; as applicable. 

Change to Paragraph (j)(3) of the 

Existing AD 

Boeing Commercial Airplanes has 

received an Organization Designation 

Authorization (ODA), which replaces 

their previous designation as a 

Delegation Option Authorization (DOA) 

holder. We have revised paragraph (j)(3) 

of the existing AD (paragraph (n)(3) of 

this AD) to delegate the authority to 

approve an alternative method of 

compliance for any repair required by 

this AD to the Boeing Commercial 

Airplanes ODA. 

Costs of Compliance 

There are about 975 airplanes of the 

affected design in the worldwide fleet. 

The following table provides the 

estimated costs for U.S. operators to 

comply with this proposed AD. 

ESTIMATED COSTS

Action Work 

hours 

Average 

labor rate 

per hour 

Parts Cost per airplane 

Number of 

U.S.-registered airplanes 

Fleet cost 

Repetitive inspections of STA 1805.5 

(required by AD 2006–24–04).

12 $80 None ........ $960 per inspection 

cycle.

354 $339,840 per inspection 

cycle. 

Inspection of inner chord (new proposed 

action).

2 $80 None ........ $160 per inspection 

cycle.

354 $56,640 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 have 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 that the 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); and 

3. 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. See the ADDRESSES section 

for a location to examine the regulatory 

evaluation. 

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 Amendment 39–14833 (71 FR 

68432, November 27, 2006) and adding 

the following new AD: 

The Boeing Company: Docket No. FAA– 

2010–0033; Directorate Identifier 2009– 

NM–099–AD. 

Comments Due Date 

(a) The FAA must receive comments on 

this AD action by March 25, 2010. 

Affected ADs 

(b) This AD supersedes AD 2006–24–04, 

Amendment 39–14833. 

Applicability 

(c) This AD applies to all The Boeing 

Company Model 767–200, –300, –300F, and 

–400ER series airplanes, certificated in any 

category. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 53: Fuselage. 

Unsafe Condition 

(e) This AD results from reported fatigue 

cracking in the vertical inner chord while 

doing a detailed inspection of the horizontal 

inner chord. The Federal Aviation 

Administration is issuing this AD to detect 

and correct fatigue cracking in the bulkhead 

structure at station (STA) 1809.5 and the 

vertical inner chord at STA 1809.5, which 

could result in failure of the bulkhead 

structure for carrying the flight loads of the 

horizontal stabilizer, and consequent loss of 

controllability of the airplane. 

Compliance 

(f) You are responsible for having the 

actions required by this AD performed within 

WReier-Aviles on DSKGBLS3C1PROD with PROPOSALS

6156 Federal Register / Vol. 75, No. 25 / Monday, February 8, 2010 / Proposed Rules 

the compliance times specified, unless the 

actions have already been done. 

Restatement of Requirements of AD 2006– 

24–04, With New Service Information 

Repetitive Inspections and Corrective 

Actions 

(g) Before the accumulation of 15,000 total 

flight cycles, or within 3,000 flight cycles 

after January 2, 2007 (the effective date of AD 

2006–24–04), whichever is later: Do the 

detailed and high frequency eddy current 

(HFEC) inspections for cracking as specified 

in Parts 1, 2, 3, and 4 of the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

767–53A0131, dated March 30, 2006; or 

Revision 1, dated March 12, 2009; and do all 

corrective actions before further flight; by 

accomplishing all the actions specified in the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 767–53A0131, dated March 

30, 2006; or Boeing Alert Service Bulletin 

767–53A0131, Revision 1, dated March 12, 

2009; except as provided by paragraph (h) of 

this AD. After the effective date of this AD, 

use only Revision 1, dated March 12, 2009, 

of Boeing Alert Service Bulletin 767– 

53A0131. Repeat the inspections thereafter at 

intervals not to exceed 6,000 flight cycles. 

Accomplishing the corrective action for the 

inspections specified in Part 1, 2, 3, or 4, as 

applicable, of Boeing Alert Service Bulletin 

767–53A0131, dated March 30, 2006; or 

Revision 1, dated March 12, 2009; as 

applicable; terminates the repetitive 

inspections for that area only. 

Exceptions to Service Bulletin 

(h) If any cracking is found in the skin or 

in any structure other than the forward outer 

chord or horizontal inner chord during any 

inspection required by paragraph (g) or (k) of 

this AD, and Boeing Service Bulletin 767– 

53A0131, dated March 30, 2006; or Boeing 

Alert Service Bulletin 767–53A0131, 

Revision 1, dated March 12, 2009; specifies 

to contact Boeing for appropriate action: 

Before further flight, repair the cracking 

using a method approved in accordance with 

the procedures specified in paragraph (n) of 

this AD. 

Optional Terminating Action for the 

Repetitive Inspections Required by 

Paragraph (g) of this AD 

(i) If no cracking is found during the most 

recent detailed and HFEC inspections for a 

specified area as required by paragraph (g) of 

this AD: Modification of a specified area in 

accordance with a method approved by the 

Manager, Seattle Aircraft Certification Office 

(ACO), FAA, terminates the repetitive 

inspections required by paragraph (g) of this 

AD for that area only. Modification of a 

forward outer chord in accordance with 

Steps 4.A through 4.C and 4.G through 4.P 

of Repair 9, dated April 15, 2006, of Chapter 

53–80–08 of the Boeing 767–200 Structural 

Repair Manual (SRM), Document D634T201; 

Boeing 767–300 SRM, Document D634T210; 

Boeing 767–300F SRM, Document D634T215; 

or Boeing 767–400 SRM, Document 

D634T225; as applicable; also terminates the 

repetitive inspections required by paragraph 

(g) of this AD for that area. Modification of 

a horizontal inner chord in accordance with 

Steps 4.A, 4.B, and 4.F through 4.P of Repair 

10, dated April 15, 2006, of Chapter 53–80– 

08 of the Boeing 767–200 SRM, Document 

D634T201; Boeing 767–300 SRM, Document 

D634T210; Boeing 767–300F SRM, Document 

D634T215; or Boeing 767–400 SRM, 

Document D634T225; as applicable; also 

terminates the repetitive inspections required 

by paragraph (g) of this AD for that area. 

Credit for Previously Accomplished Repairs 

(j) Repair of a forward outer chord done 

before January 2, 2007, in accordance with 

Repair 9, dated April 15, 2006, of Chapter 

53–80–08 of the Boeing 767–200 SRM, 

Document D634T201; Boeing 767–300 SRM, 

Document D634T210; Boeing 767–300F SRM, 

Document D634T215; or Boeing 767–400 

SRM, Document D634T225; as applicable; is 

acceptable for compliance with the 

requirements of paragraph (g) of this AD for 

that area only. Repair of a horizontal inner 

chord before January 2, 2007, in accordance 

with Repair 10, dated April 15, 2006, of 

Chapter 53–80–08 of the Boeing 767–200 

SRM, Document D634T201; Boeing 767–300 

SRM, Document D634T210; Boeing 767–300F 

SRM, Document D634T215; or Boeing 767– 

400 SRM, Document D634T225; as 

applicable; is acceptable for compliance with 

the requirements of paragraph (g) of this AD 

for that area only. 

New Requirements of This AD 

Inspections 

(k) At the later of the times specified in 

paragraphs (k)(1) and (k)(2) of this AD, except 

as specified in paragraph (l) of this AD: Do 

the detailed and HFEC inspections for 

cracking as specified in Parts 5 and 6 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 767–53A0131, Revision 1, 

dated March 12, 2009; and do all applicable 

corrective actions by accomplishing all the 

actions specified in the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

767–53A0131, Revision 1, dated March 12, 

2009; except as provided by paragraph (h) of 

this AD. Do all applicable corrective actions 

before further flight. Repeat the inspections 

thereafter at intervals not to exceed 6,000 

flight cycles. Accomplishing the corrective 

action for the inspections specified in Part 5 

or 6 of the Accomplishment Instructions of 

Boeing Alert Service Bulletin 767–53A0131, 

Revision 1, dated March 12, 2009, as 

applicable, terminates the repetitive 

inspections for that area only. 

(1) 15,000 total flight cycles or 6,000 flight 

cycles after the inspection required by 

paragraph (g) of this AD, whichever occurs 

first. 

(2) 30 days after the effective date of this 

AD. 

Exceptions to the Service Bulletin 

(l) Where Boeing Alert Service Bulletin 

767–53A0131, Revision 1, dated March 12, 

2009, specifies a compliance time ‘‘after the 

date on the original issue of the service 

bulletin’’ or ‘‘after the date on Revision 01 of 

the service bulletin,’’ this AD requires 

compliance within the specified compliance 

time after the effective date of this AD. 

Optional Terminating Action for the 

Repetitive Inspections Required by 

Paragraph (k) of This AD 

(m) If no cracking is found during the most 

recent detailed and HFEC inspections for a 

specified area as required by paragraph (k) of 

this AD: Modification of a specified area in 

accordance with a method approved by the 

Manager, Seattle ACO, FAA, terminates the 

repetitive inspections required by paragraph 

(k) of this AD for that area only. 

Note 1: Guidance on modifying a vertical 

inner chord can be found in the service 

information identified in Table 1 of this AD. 

TABLE 1—SERVICE INFORMATION

Steps— Dated— Of— 

4.A through 4.C and 4.G through 4.Q of Repair 11 ............. August 15, 2008 ........ Chapter 53-80–08 of the Boeing 767–200 SRM, Document 

D634T201. 

4.A through 4.C and 4.G through 4.Q of Repair 11 ............. August 15, 2008 ........ Chapter 53-80–08 of the Boeing 767–300 SRM, Document 

D634T210. 

4.A through 4.C and 4.G through 4.Q of Repair 11 ............. August 15, 2008 ........ Chapter 53-80–08 of the Boeing 767–300F SRM, Document D634T215. 

4.A through 4.C and 4.G through 4.Q of Repair 11 ............. August 15, 2008 ........ Chapter 53-80–08 of the Boeing 767–400 SRM, Document 

D634T225. 

WReier-Aviles on DSKGBLS3C1PROD with PROPOSALS

Federal Register / Vol. 75, No. 25 / Monday, February 8, 2010 / Proposed Rules 6157 

Alternative Methods of Compliance 

(AMOCs) 

(n)(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. Send information to ATTN: 

Berhane Alazar, Airframe Branch, ANM– 

120S, FAA, Seattle Aircraft Certification 

Office, 1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone (425) 

917–6577; fax (425) 917–6590. Or, e-mail 

information to 9–ANM–Seattle–ACO–AMOC– 

Requests@faa.gov. 

(2) To request a different method of 

compliance or a different compliance time 

for this AD, follow the procedures in 14 CFR 

39.19. Before using any approved AMOC on 

any airplane to which the AMOC applies, 

notify your principal maintenance inspector 

(PMI) or principal avionics inspector (PAI), 

as appropriate, or lacking a principal 

inspector, your local Flight Standards District 

Office. The AMOC approval letter must 

specifically reference this AD. 

(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. 

(4) AMOCs approved previously in 

accordance with AD 2006–24–04 are 

approved as AMOCs for the corresponding 

provisions of this AD. 

Issued in Renton, Washington, on January 

28, 2010. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–2685 Filed 2–5–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0034; Directorate 

Identifier 2009–NM–120–AD] 

RIN 2120–AA64 

Airworthiness Directives; Gulfstream 

Aerospace LP Model Gulfstream 100 

Airplanes, and Model Astra SPX and 

1125 Westwind Astra Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for the 

products listed above that would 

supersede an existing AD. This 

proposed AD results from mandatory 

continuing airworthiness information 

(MCAI) originated by an aviation 

authority of another country to identify 

and correct an unsafe condition on an 

aviation product. The MCAI describes 

the unsafe condition as: Incomplete 

closure of the MED [main entry door] 

may be followed by in-flight opening of 

the door. As a result, the MED and the 

adjacent fuselage structure may be 

damaged during opening and landing 

impact. Damage to the left engine by 

flying debris and objects may also occur. 

The proposed AD would require 

actions that are intended to address the 

unsafe condition described in the MCAI. 

DATES: We must receive comments on 

this proposed AD by March 25, 2010. 

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 

W12–40, 1200 New Jersey Avenue, SE., 

Washington, DC, between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For Gulfstream service information 

identified in this proposed AD, contact 

Gulfstream Aerospace Corporation, P.O. 

Box 2206, Mail Station D–25, Savannah, 

Georgia 31402–2206; telephone 800– 

810–4853; fax 912–965–3520; e-mail 

pubs@gulfstream.com; Internet http:// 

www.gulfstream.com/product_support/ 

technical_pubs/pubs/index.htm. For 

Honeywell service information 

identified in this proposed AD, contact 

Honeywell Aerospace, Technical 

Publications and Distribution, M/S 

2101–201, P.O. Box 52170, Phoenix, 

Arizona 85072–2170; telephone 602– 

365–5535; fax 602–365–5577; Internet 

http://www.honeywell.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 

or 425–227–1152. 

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: 

Mike Borfitz, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 227–2677; fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2010–0034; Directorate Identifier 

2009–NM–120–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD based on those comments. 

We have lengthened the 30-day 

comment period for proposed ADs that 

address MCAI originated by aviation 

authorities of other countries to provide 

adequate time for interested parties to 

submit comments. The comment period 

for these proposed ADs is now typically 

45 days, which is consistent with the 

comment period for domestic transport 

ADs. 

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 

On January 23, 2007, we issued AD 

2007–03–05, Amendment 39–14916 (72 

FR 4414, January 31, 2007). That AD 

required actions intended to address an 

unsafe condition on the products listed 

above. 

Since we issued AD 2007–03–05, the 

Civil Aviation Administration of Israel 

(CAAI), which is the aviation authority 

for Israel, has issued Israeli 

Airworthiness Directive 31–06–11–05, 

dated May 27, 2009 (referred to after 

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

condition for the specified products. 

The MCAI states: 

To increase pilots’ awareness to the 

possibility of incomplete closure of the Main 

Entry Door (MED) by the following means: 

WReier-Aviles on DSKGBLS3C1PROD with PROPOSALS