Federal Register / Vol. 77, No. 162 / Tuesday, August 21, 2012 / Proposed Rules 50411 

February 14, 2011, to accomplish the 

modifications required by this paragraph. 

(j) Retained Action for Airplanes on Which 

Modifications Were Accomplished 

Previously 

This paragraph restates the requirements of 

paragraph (d) of AD 2000–07–06, 

Amendment 39–11660 (65 FR 19302, April 

11, 2000). For all airplanes on which 

modifications of the forward lower corner of 

the door frame and the cross beam of the 

forward cargo door were accomplished in 

accordance with Boeing Service Bulletin 

737–52–1100, dated August 25, 1988, or 

Revision 1, dated July 20, 1989; or in 

accordance with the requirements of AD 90– 

06–02, Amendment 39–6489 (55 FR 8372, 

March 7, 1990): Within 4 years or 12,000 

flight cycles after May 16, 2000 (the effective 

date of AD 2000–07–06), whichever occurs 

later, install the reinforcement modification 

of the aft corner of the door frame of the 

forward cargo door, in accordance with 

Boeing Service Bulletin 737–52–1100, 

Revision 2, dated March 31, 1994. 

Accomplishment of such modification 

constitutes terminating action for the 

repetitive inspections required by paragraphs 

(g)(1) and (h)(1) of this AD. 

(k) New Inspections and Corrective Actions 

Except as provided by paragraphs (m)(1) 

and (m)(2) of this AD: At the applicable time 

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

Boeing Alert Service Bulletin 737–52A1100, 

Revision 5, dated February 14, 2011, do the 

inspections required by paragraphs (k)(1) and 

(k)(2) of this AD, as applicable. Do all 

applicable related investigative and 

corrective actions before further flight, in 

accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

737–52A1100, Revision 5, dated February 14, 

2011; except as required by paragraph (m)(3) 

of this AD. Accomplishment of the 

inspections required by paragraph (k) of this 

AD terminates the requirements of the 

repetitive inspections required by paragraphs 

(g)(1) and (h)(1) of this AD. If any cracking 

is found in the number 4 cross beam, before 

further flight, repair in accordance with 

Boeing Special Attention Service Bulletin 

737–52–1149, dated December 11, 2003. 

Note 2 to paragraph (k) of this AD: Boeing 

Alert Service Bulletin 737–52A1100, 

Revision 5, dated February 14, 2011, refers to 

Boeing Special Attention Service Bulletin 

737–52–1149, dated December 11, 2003, as 

an additional source of guidance for the 

inspection for cracks of the number 4 cross 

beam. 

(1) For airplanes identified in Tables 1 and 

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

Alert Service Bulletin 737–52A1100, 

Revision 5, dated February 14, 2011: Do a 

one-time HFEC inspection of the applicable 

location for cracks, in accordance with the 

Work Instructions, Part I, of Boeing Alert 

Service Bulletin 737–52A1100, Revision 5, 

dated February 14, 2011. 

(2) For airplanes identified in Table 3 of 

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

Service Bulletin 737–52A1100, Revision 5, 

dated February 14, 2011: Do a one-time 

general visual inspection of the 

reinforcement angle for excessive shimming 

or fastener pull-up, in accordance with the 

Work Instructions, Part III, of Boeing Alert 

Service Bulletin 737–52A1100, Revision 5, 

dated February 14, 2011. 

(l) No Supplemental Structural Inspections 

Required by This AD 

(1) The supplemental structural 

inspections specified in Table 4 of paragraph 

1.E., ‘‘Compliance,’’ and Part 5 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 737–52A1100, Revision 5, 

dated February 14, 2011, are not required by 

this AD. 

(2) The supplemental structural 

inspections specified in Table 4 of paragraph 

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

Bulletin 737–52A1100, Revision 5, dated 

February 14, 2011, may be used in support 

of compliance with section 121.1109(c)(2) or 

129.109(c)(2) of the Federal Aviation 

Regulations (14 CFR 121.1109(c)(2) or 14 CFR 

129.109(c)(2)). The corresponding actions 

specified in the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

737–52A1100, Revision 5, dated February 14, 

2011, are not required by this AD. 

(m) Exceptions to Certain Service 

Information 

(1) Where paragraph 1.E., ‘‘Compliance,’’ of 

Boeing Alert Service Bulletin 737–52A1100, 

Revision 5, dated February 14, 2011, 

specifies a compliance time relative to the 

Revision 5 issue date of the service bulletin, 

this AD requires compliance within the 

specified compliance time after the effective 

date of this AD. 

(2) Where Table 1, ‘‘Condition’’ column of 

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

Alert Service Bulletin 737–52A1100, 

Revision 5, dated February 14, 2011, 

specifies ‘‘airplanes without either the repair 

or modification accomplished in accordance 

with previous releases of this service 

bulletin,’’ the corresponding condition in this 

AD is for ‘‘airplanes on which either a repair 

or modification was not accomplished before 

the effective date of this AD.’’ 

(3) Where Boeing Alert Service Bulletin 

737–52A1100, Revision 5, dated February 14, 

2011, specifies to contact Boeing for certain 

actions: Before further flight, do the repair 

using a method approved in accordance with 

the procedures specified in paragraph (n)(1) 

of this AD. 

(n) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle ACO, has the 

authority to approve AMOCs for this AD, if 

requested using the procedures found in 14 

CFR 39.19. In accordance with 14 CFR 39.19, 

send your request to your principal inspector 

or local Flight Standards District Office, as 

appropriate. If sending information directly 

to the manager of the ACO, send it to the 

attention of the person identified in the 

Related Information section of this AD. 

Information may be emailed to: 9-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 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 2000–07–06, 

Amendment 39–11660 (65 FR 19302, April 

11, 2000), are approved as AMOCs for the 

corresponding requirements of this AD. 

(o) Related Information 

(1) For more information about this AD, 

contact Alan Pohl, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, Seattle 

ACO, 1601 Lind Avenue SW., Renton, 

Washington 98057–3356; phone (425) 917– 

6450; fax (425) 917–6590; email 

alan.pohl@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 August 

13, 2012. 

John P. Piccola, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2012–20470 Filed 8–20–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0856; Directorate 

Identifier 2012–NM–093–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 747–100, 

747–100B, 747–100B SUD, 747–200B, 

747–200F, 747–300, 747–400, 747– 

400D, 747–400F, 747SR, and 747SP 

series airplanes; Model 767–200, –300, 

–300F, and –400ER series airplanes; and 

Model 777–200, –200LR, –300, and 

–300ER series airplanes. This proposed 


pmangrum on DSK3VPTVN1PROD with PROPOSALS-1
50412 Federal Register / Vol. 77, No. 162 / Tuesday, August 21, 2012 / Proposed Rules 

AD was prompted by reports of burned 

Boeing Material Specification (BMS) 8– 

39 urethane foam, and a report from the 

airplane manufacturer that airplanes 

were assembled with seals throughout 

various areas of the airplane (including 

flight deck and cargo compartments) 

made of BMS 8–39 urethane foam, a 

material with fire-retardant properties 

that deteriorate with age. This proposed 

AD would require replacing seals made 

of BMS 8–39 urethane foam in certain 

areas of the airplane. We are proposing 

this AD to prevent the failure of 

urethane seals to maintain sufficient 

Halon concentrations in the cargo 

compartments to extinguish or contain 

fire or smoke, and to prevent 

penetration of fire or smoke in areas of 

the airplane that are difficult to access 

for fire and smoke detection or 

suppression. 

DATES: We must receive comments on 

this proposed AD by October 5, 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, 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: Eric 

M. Brown, Aerospace Engineer, Cabin 

Safety and Environmental Systems 

Branch, ANM–150S, FAA, Seattle 

Aircraft Certification Office, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

phone: 425–917–6476; fax: 425–917– 

6590; email: Eric.M.Brown@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– 

2012–0856; Directorate Identifier 2012– 

NM–093–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 burned 

BMS 8–39 urethane foam insulation on 

two Model 767–200 series airplanes. 

The airplane manufacturer has also 

notified us that certain Model 747, 767, 

and 777 airplanes were assembled with 

seals throughout various areas of the 

airplane (including flight deck and 

cargo compartments) made of BMS 8–39 

urethane foam. The fire retardants in 

BMS 8–39 urethane foam are mixed 

into, but are not chemically connected 

with, the remaining components of the 

foam. The fire-retardant properties of 

BMS 8–39 urethane foam deteriorate 

with age (5 to 10 years). This, along with 

dust, dirt, and other carbon particulate 

contamination of the urethane foam, 

adds an available fuel source for a 

potential fire. Once ignited, the 

deteriorated foam emits noxious smoke, 

does not self-extinguish, and drips 

droplets of liquefied urethane, which 

can further propagate a fire. Deteriorated 

BMS 8–39 urethane foam seals in a 

cargo compartment also compromise the 

Halon retention and smoke/fire-blocking 

capabilities of the cargo compartment. 

These conditions, if not corrected, could 

result in failure of urethane seals to 

maintain sufficient Halon 

concentrations in the cargo 

compartments to extinguish or contain 

fire or smoke, and could result in 

penetration of fire or smoke in areas of 

the airplane that are difficult to access 

for fire and smoke detection or 

suppression. 

Other Relevant Rulemaking 

We issued the following ADs to 

require reworking certain air 

distribution ducts in the environmental 

control system (ECS) wrapped with 

BMS 8–39 or Aeronautical Materials 

Specifications (AMS) 3570 urethane 

foam insulation. These ADs resulted 

from reports from the airplane 

manufacturer that airplanes were 

assembled with duct assemblies in the 

ECS wrapped with BMS 8–39 urethane 

foam insulation, a material with fireretardant properties that deteriorate 

with age, and reports of duct assemblies 

in the ECS with burned BMS 8–39 

urethane foam insulation. We issued 

these ADs to prevent a potential 

electrical arc from igniting the BMS 8– 

39 urethane foam insulation on the duct 

assemblies of the ECS, which could 

propagate a small fire and lead to a 

larger fire that might spread throughout 

the airplane through the ECS. 

• AD 2008–02–16, Amendment 39– 

15346 (73 FR 4061, January 24, 2008), 

applicable to certain Model 767–200 

and 767–300 series airplanes. 

• AD 2010–14–01, Amendment 39– 

16344 (75 FR 38007, July 1, 2010), 

applicable to certain Model 747–100, 

747–100B, 747–100B SUD, 747–200B, 

747–200C, 747–200F, 747–300, 747– 

400, 747–400F, 747SR, and 747SP series 

airplanes. 

• AD 2012–02–09, Amendment 39– 

16932 (77 FR 5996, February 7, 2012), 

for certain Model 737–100, –200, –200C, 

and –300 series airplanes. 

Relevant Service Information 

We reviewed the following Boeing 

service bulletins: 

• For Model 747–100, 747–100B, 

747–100B SUD, 747–200B, 747–200F, 

747–300, 747–400, 747–400D, 747– 

400F, 747SR, and 747SP series 

airplanes: Boeing Special Attention 

Service Bulletin 747–25–3381, Revision 

1, dated May 17, 2012. This service 

bulletin describes procedures for 

replacing BMS 8–39 urethane foam seals 

with either BMS 8–371 insulation foam 

or BMS 1–68 silicone foam rubber seals. 

(The required actions depend on 

requirements for use and location of the 

BMS 8–39 urethane foam in the 

airplane.) Procedures for the 

replacement include, for some 

airplanes, doing a general visual 


pmangrum on DSK3VPTVN1PROD with PROPOSALS-1
Federal Register / Vol. 77, No. 162 / Tuesday, August 21, 2012 / Proposed Rules 50413 

inspection of the airplane sidewalls for 

air baffles, and of the BMS 8–39 

urethane foam for penetrations (e.g., 

wire penetrations). The replacement is 

to be done in the following areas of the 

airplane (depending on airplane 

configuration): 

• Main deck system tube/wire foam 

seals (left/right sidewalls) 

• Main deck foam air seal (left/right 

sidewalls) 

• Main deck air baffle foam (left/right 

sidewalls) 

• Main deck ceiling panel foam strip 

• Forward and aft cargo system tube/ 

wire foam seal 

• Flight deck overheard electrical 

equipment panel/structure and 

overhead drip-shield foam 

• E1/E2 rack wire integration unit 

cover assemblies 

• For Model 767–200, –300, –300F, 

and –400ER series airplanes: Boeing 

Special Attention Service Bulletin 767– 

25–0381, dated August 19, 2010. This 

service bulletin describes procedures for 

doing a general visual inspection for 

BMS 8–39 urethane foam for certain 

airplanes, covering the BMS 8–39 foam 

with cargo liner joint sealing tape in 

certain areas, replacing certain BMS 8– 

39 foam pads with Nomex felt in certain 

areas, and replacing BMS 8–39 urethane 

foam seals with either BMS 8–371 

insulation foam or BMS 1–68 silicone 

foam rubber seals. (The required actions 

depend on requirements for use and 

location of the BMS 8–39 urethane foam 

in the airplane.) The actions are to be 

done in the following areas of the 

airplane (depending on airplane 

configuration): 

• Forward and aft cargo 

compartments 

• Flight deck 

• Crown area (foam pad to be 

replaced with Nomex felt) 

• Over wing escape hatch (corner 

seals) 

• For Model 777–200, –200LR, –300, 

and –300ER series airplanes: Boeing 

Special Attention Service Bulletin 777– 

25–0362, dated August 19, 2010. This 

service bulletin describes procedures for 

replacing BMS 8–39 urethane foam seals 

with BMS 1–68 silicone foam rubber 

seals in the forward and aft cargo 

compartments of the airplane. 

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. 

Costs of Compliance 

We estimate that this proposed AD 

affects 694 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 

Replacement for Model 747 airplanes, depending on airplane configuration (165 

airplanes).

Up to 432 work-hours × $85 

per hour = $36,720.

Up to $6,162 ........... Up to $42,882 ......... Up to $7,075,530. 

Replacement for Model 767 airplanes, depending on airplane configuration (399 

airplanes).

Up to 72 work-hours × $85 per 

hour = $6,120.

Up to $3,967 ........... Up to $10,087 ......... Up to $4,024,713. 

Replacement for Model 777 airplanes (130 

airplanes).

16 work-hours × $85 per hour 

= $1,360.

$1,038 ..................... $2,398 ..................... $311,740. 

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– 

2012–0856; Directorate Identifier 2012– 

NM–093–AD. 


pmangrum on DSK3VPTVN1PROD with PROPOSALS-1
50414 Federal Register / Vol. 77, No. 162 / Tuesday, August 21, 2012 / Proposed Rules 

(a) Comments Due Date 

We must receive comments by October 5, 

2012. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to The Boeing Company 

airplanes, certificated in any category, 

identified in paragraphs (c)(1), (c)(2), and 

(c)(3) of this AD. 

(1) Model 747–100, 747–100B, 747–100B 

SUD, 747–200B, 747–200F, 747–300, 747– 

400, 747–400D, 747–400F, 747SR, and 747SP 

series airplanes, as identified in Boeing 

Special Attention Service Bulletin 747–25– 

3381, Revision 1, dated May 17, 2012. 

(2) Model 767–200, –300, –300F, and 

–400ER series airplanes, as identified in 

Boeing Special Attention Service Bulletin 

767–25–0381, dated August 19, 2010. 

(3) Model 777–200, –200LR, –300, and 

–300ER series airplanes, as identified in 

Boeing Special Attention Service Bulletin 

777–25–0362, dated August 19, 2010. 

(d) Subject 

Joint Aircraft System Component (JASC)/ 

Air Transport Association (ATA) of America 

Code 25, Equipment/furnishings. 

(e) Unsafe Condition 

This AD was prompted by reports of 

burned Boeing Material Specification (BMS) 

8–39 urethane foam, and a report from the 

airplane manufacturer that airplanes were 

assembled with seals throughout various 

areas of the airplane (including flight deck 

and cargo compartments) made of BMS 8–39 

urethane foam, a material with fire-retardant 

properties that deteriorate with age. We are 

issuing this AD to prevent the failure of 

urethane seals to maintain sufficient Halon 

concentrations in the cargo compartments to 

extinguish or contain fire or smoke, and to 

prevent penetration of fire or smoke in areas 

of the airplane that are difficult to access for 

fire and smoke detection or suppression. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) BMS 8–39 Urethane Foam Seal 

Replacements 

Within 72 months after the effective date 

of this AD, do the actions specified in 

paragraph (g)(1), (g)(2), or (g)(3) of this AD, 

as applicable. 

(1) For Model 747–100, 747–100B, 747– 

100B SUD, 747–200B, 747–200F, 747–300, 

747–400, 747–400D, 747–400F, 747SR, and 

747SP series airplanes: Replace the BMS 8– 

39 urethane foam seals (including doing a 

general visual inspection of the airplane 

sidewalls for air baffles, and of the BMS 8– 

39 urethane foam for penetrations (e.g., wire 

penetrations)) with BMS 8–371 insulation 

foam or BMS 1–68 silicone foam rubber seals, 

as applicable, in accordance with the 

Accomplishment Instructions and Appendix 

A, as applicable, of Boeing Special Attention 

Service Bulletin 747–25–3381, Revision 1, 

dated May 17, 2012. 

(2) For Model 767–200, –300, –300F, and 

–400ER series airplanes: Perform a general 

visual inspection for the presence of BMS 8– 

39 urethane foam, cover the BMS 8–39 foam 

with cargo liner joint sealing tape in certain 

areas, replace certain BMS 8–39 foam pads 

with Nomex felt in certain areas, and replace 

BMS 8–39 urethane foam seals with BMS 8– 

371 insulation foam or BMS 1–68 silicone 

foam rubber seals, as applicable, in 

accordance with the Accomplishment 

Instructions and Appendix A, as applicable, 

of Boeing Special Attention Service Bulletin 

767–25–0381, dated August 19, 2010. 

(3) For Model 777–200, –200LR, –300, and 

–300ER series airplanes: Replace BMS 8–39 

urethane foam seals with BMS 1–68 silicone 

foam rubber seals in the forward and aft 

cargo compartments of the airplane, in 

accordance with the Accomplishment 

Instructions of Boeing Special Attention 

Service Bulletin 777–25–0362, dated August 

19, 2010. 

(h) Credit for Previous Actions 

For Groups 4 and 5 airplanes, as identified 

in Boeing Special Attention Service Bulletin 

747–25–3381, Revision 1, dated May 17, 

2012: This paragraph provides credit for the 

actions required by paragraph (g)(1) of this 

AD, if those actions were done before the 

effective date of this AD using Boeing Special 

Attention Service Bulletin 747–25–3381, 

dated August 19, 2010. 

(i) Parts Installation Prohibition 

As of the effective date of this AD, no 

person may install a BMS 8–39 urethane 

foam seal on any airplane. 

(j) 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. 

(k) Related Information 

(1) For more information about this AD, 

contact Eric M. Brown, 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– 

6476; fax: 425–917–6590; email: 

Eric.M.Brown@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 August 

9, 2012. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–20473 Filed 8–20–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0857; Directorate 

Identifier 2011–NM–244–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 737–100, 

–200, –200C, –300, –400, and –500 

series airplanes. This proposed AD was 

prompted by a report of an approximate 

8-inch crack found in the fuselage skin 

under the aft drain mast. This proposed 

AD would require a detailed inspection 

for cracking and corrosion of the 

channel and fillers adjacent to the drain 

mast bolts, an inspection to determine 

the location of the bonding strap, a 

measurement of the washers under the 

drain mast bolts, and related 

investigative actions and repair if 

necessary. We are proposing this AD to 

detect and correct cracking in the 

fuselage skin and internal support 

structure, which could result in 

uncontrolled decompression of the 

airplane. 

DATES: We must receive comments on 

this proposed AD by October 5, 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. 


pmangrum on DSK3VPTVN1PROD with PROPOSALS-1