15640 Federal Register / Vol. 77, No. 52 / Friday, March 16, 2012 / Proposed Rules 

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– 

2009–0288; Directorate Identifier 2008– 

NM–214–AD. 

(a) Comments Due Date 

We must receive comments by April 30, 

2012. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to The Boeing Company 

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

–900ER series airplanes, certificated in any 

category, as identified in Boeing Special 

Attention Service Bulletin 737–57–1293, 

Revision 2, dated September 28, 2011. 

(d) Subject 

Joint Aircraft System Component (JASC)/ 

Air Transport Association (ATA) of America 

Code 57, Wings. 

(e) Unsafe Condition 

This AD was prompted by a report of 

leaking fuel from the wing leading edge area 

at the inboard end of the number 5 leading 

edge slat. We are issuing this AD to prevent 

flammable fluids from accumulating in the 

wing leading edge, and draining inboard and 

onto the engine exhaust nozzle, which could 

result in a fire. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Modification 

Within 24 months after the effective date 

of this AD, modify the fluid drain path in the 

wing leading edge area, forward of the wing 

front spar, and do all applicable related 

investigative and corrective actions, by 

accomplishing all applicable actions 

specified in the Accomplishment 

Instructions of Boeing Special Attention 

Service Bulletin 737–57–1293, Revision 2, 

dated September 28, 2011. Do all applicable 

related investigative and corrective actions 

before further flight. 

(h) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle Aircraft 

Certification Office, 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. 

(i) Related Information 

(1) For more information about this AD, 

contact Chris R. Parker, Aerospace Engineer, 

Propulsion Branch, ANM–140S, FAA, Seattle 

Aircraft Certification Office, 1601 Lind 

Avenue SW., Renton, Washington 98057– 

3356; phone: 425–917–6496; fax: 425–917– 

6590; email: chris.r.parker@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 February 

23, 2012. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–6468 Filed 3–15–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0036; Directorate 

Identifier 2009–NM–077–AD] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Supplemental notice of 

proposed rulemaking (NPRM); 

reopening of comment period. 

SUMMARY: We are revising an earlier 

proposed airworthiness directive (AD) 

for certain The Boeing Company Model 

737–200, –200C, –300, –400, and –500 

series airplanes. That NPRM proposed 

to require inspections for cracking and 

corrosion under the number 3 very high 

frequency (VHF) antenna, and corrective 

actions if necessary; and, for certain 

airplanes, replacing bonded skin panels 

with solid skin panels if not previously 

accomplished. That NPRM was 

prompted by reports of cracks in the 

skin and surrounding structure under 

the number 3 VHF antenna on the lower 

external surface of the airplane at 

buttock line 0.0, aft of the main landing 

gear wheel well. This action revises that 

NPRM by adding an optional preventive 


tkelley on DSK3SPTVN1PROD with PROPOSALS
Federal Register / Vol. 77, No. 52 / Friday, March 16, 2012 / Proposed Rules 15641 

modification, which would terminate 

the inspection requirements for certain 

airplanes; changing certain repairs; and 

adding inspections. We are proposing 

this supplemental NPRM to detect and 

correct cracks and corrosion of the skin 

and surrounding structure under the 

number 3 VHF antenna, which could 

result in separation of the antenna from 

the airplane, and rapid depressurization 

of the airplane. Since these actions 

impose an additional burden over that 

proposed in the original NPRM, we are 

reopening the comment period to allow 

the public the chance to comment on 

these proposed changes. 

DATES: We must receive comments on 

this supplemental NPRM by April 30, 

2012. 

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 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: 

Wayne Lockett, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue SW., Renton, 

Washington 98057–3356; phone: (425) 

917–6447; fax: (425) 917–6590; email: 

wayne.lockett@faa.gov. 

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–2010–0036; Directorate Identifier 

2009–NM–077–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 issued an NPRM to amend 14 CFR 

part 39 to include an airworthiness 

directive (AD) that would apply to 

certain The Boeing Company Model 

737–200, –200C, –300, –400, and –500 

series airplanes. That original NPRM 

was published in the Federal Register 

on April 15, 2010 (75 FR 19564). That 

original NPRM proposed to require 

repetitive inspections for cracking and 

corrosion of the skin and surrounding 

structure under the number 3 VHF 

antenna, and corrective actions if 

necessary. Also, for certain airplanes, 

that original NPRM proposed to require 

replacing bonded skin panels with solid 

skin panels if not previously 

accomplished. 

Actions Since Previous NPRM (75 FR 

19564, April 15, 2010) Was Issued 

The original NPRM (75 FR 19564, 

April 15, 2010) referred to Boeing 

Special Attention Service Bulletin 737– 

53–1287, dated March 11, 2009. Since 

we issued the original NPRM, we have 

reviewed Boeing Special Attention 

Service Bulletin 737–53–1287, Revision 

1, dated November 15, 2010. Among 

other things, this service bulletin 

provides the following changes: 

• Adds an optional preventive 

modification for certain airplane groups, 

which would eliminate the need for the 

repetitive inspections of those airplanes. 

The modification involves various high 

frequency eddy current (HFEC) and 

detailed inspections for cracking and 

corrosion of the skin, support channel, 

holes, and support structure in the area 

of the number 3 VHF antenna; and 

repair if necessary, or replacing a 

cracked or corroded support channel 

with a new or serviceable support 

channel, if necessary. The modification 

also entails installing antenna support 

structure. 

• Reassigns certain airplanes to 

different groups. 

• Gives instructions for doing repairs 

if a crack is found, for certain airplane 

groups and certain conditions. 

• Adds HFEC inspections (that are 

done along with previously specified 

internal detailed inspections) with the 

antenna removed. 

• Adds Group 7 airplanes (line 

numbers 1–291) and specifies that, for 

these airplanes, operators must contact 

Boeing for inspection, repair, and 

preventive modification instructions. 

These airplanes are subject to a prior or 

concurrent action of replacing bonded 

skin panels with solid skin panels, as 

specified in Part V of Boeing Service 

Bulletin 737–53A1042, Revision 9, 

dated July 25, 1991. (The actions 

specified in that service bulletin are 

already required by AD 90–06–02, 

Amendment 39–6489 (55 FR 8372, 

March 7, 1990)). 

Comments 

We gave the public the opportunity to 

comment on the original NPRM (75 FR 

19564, April 15, 2010). The following 

presents the comment received on the 

NPRM and the FAA’s response to the 

comment. 

Request To Change Requirements for 

Certain Airplanes 

Boeing submitted a comment related 

to the service information. However, the 

substance of the comment is addressed 

in Boeing Special Attention Service 

Bulletin 737–53–1287, Revision 1, dated 

November 15, 2010 as discussed above 

in ‘‘Actions Since Previous NPRM (75 

FR 19564, April 15, 2010) Was Issued.’’ 

FAA’s Determination 

We are proposing this supplemental 

NPRM 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. Certain changes described 

above expand the scope of the original 


tkelley on DSK3SPTVN1PROD with PROPOSALS
15642 Federal Register / Vol. 77, No. 52 / Friday, March 16, 2012 / Proposed Rules 

NPRM (75 FR 19564, April 15, 2010). As 

a result, we have determined that it is 

necessary to reopen the comment period 

to provide additional opportunity for 

the public to comment on this 

supplemental NPRM. 

Proposed Requirements of the 

Supplemental NPRM 

This supplemental NPRM would 

require accomplishing the actions 

specified in the revised service 

information described previously, 

except as discussed under ‘‘Differences 

Between the Supplemental NPRM and 

the Service Information.’’ 

Differences Between the Supplemental 

NPRM and the Service Information 

Where paragraph 1.A., ‘‘Effectivity,’’ 

of Boeing Special Attention Service 

Bulletin 737–53–1287, Revision 1, dated 

November 15, 2010, places Model 737– 

200 and –200C airplanes having line 

numbers 1–291 into group 7, for 

purposes of this supplemental NPRM, 

these airplanes would be subject to the 

proposed requirements for Group 2, 

Configuration 1, 2, or 3, as applicable. 

There are no configuration differences 

for airplanes having line numbers 1–291 

from the Group 2 airplanes. 

Table 10 in paragraph 1.E., 

‘‘Compliance,’’ of Boeing Special 

Attention Service Bulletin 737–53– 

1287, Revision 1, dated November 15, 

2010; and Part 8 of the Accomplishment 

Instructions of Boeing Special Attention 

Service Bulletin 737–53–1287, Revision 

1, dated November 15, 2010; specify 

post-repair/modification inspections at 

the number 3 VHF antenna location, 

which 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 

129.109(c)(2)), but this supplemental 

NPRM does not propose to require those 

post-repair/modification inspections. 

This difference has been coordinated 

with Boeing. 

Costs of Compliance 

We estimate that this proposed AD 

will affect 629 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 

Number of 

U.S.- 

registered 

airplanes 

Cost on U.S. operators 

Inspection .......................... Up to 13 work-hours × 

$85 per hour = Up to 

$1,105 per inspection 

cycle.

None ........... Up to $1,105 per inspection cycle.629 Up to $695,045 per inspection cycle. 

Concurrent Replacement 

for Group 2 and Group 7 

airplanes 1.

2,112 work-hours × $85 

per hour = $179,520.

$35,000 ....... $214,520 ......................... 387 $83,019,240. 

1The concurrent modification for Group 2 and Group 7 airplanes required by this proposed AD is already required by AD 90–06–02, Amendment 39–6489 (55 FR 8372, March 7, 1990). AD 90–06–02 mandated the skin replacement within 20 years of the manufacture date of the airplane. All Group 2 and Group 7 airplanes have exceeded the 20-year threshold. 

We have received no definitive data 

that would enable us to provide a cost 

estimate for the on-condition actions 

specified in this AD. 

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– 

2010–0036; Directorate Identifier 2009– 

NM–077–AD. 

(a) Comments Due Date 

We must receive comments by April 30, 

2012. 


tkelley on DSK3SPTVN1PROD with PROPOSALS
Federal Register / Vol. 77, No. 52 / Friday, March 16, 2012 / Proposed Rules 15643 

(b) Affected ADs 

AD 90–06–02, Amendment 39–6489 (55 FR 

8372, March 7, 1990), affects this AD. 

(c) Applicability 

This AD applies to The Boeing Company 

Model 737–200, –200C, –300, –400, –500 

series airplanes, certificated in any category, 

as identified in Boeing Special Attention 

Service Bulletin 737–53–1287, Revision 1, 

dated November 15, 2010. 

(d) Subject 

Joint Aircraft System Component (JASC)/ 

Air Transport Association (ATA) of America 

Code 53: Fuselage. 

(e) Unsafe Condition 

This AD was prompted by reports of cracks 

of the skin and surrounding structure under 

the number 3 very high frequency (VHF) 

antenna on the lower external surface of the 

airplane at buttock line 0.0, aft of the main 

landing gear wheel well. We are issuing this 

AD to detect and correct cracks and corrosion 

of the skin and surrounding structure under 

the number 3 VHF antenna, which could 

result in separation of the antenna from the 

airplane, and rapid depressurization of the 

airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspections 

Except as required by paragraph (i)(1) of 

this AD, at the applicable times specified in 

tables 1 through 9, paragraph 1.E., 

‘‘Compliance,’’ of Boeing Special Attention 

Service Bulletin 737–53–1287, Revision 1, 

dated November 15, 2010: Do the applicable 

inspections (external detailed and high 

frequency eddy current (HFEC), external 

detailed, external HFEC, or internal detailed 

and HFEC) for cracks or corrosion in the skin, 

support, frames, stringers, or antenna, as 

applicable. Do the inspections in accordance 

with Parts 1, 3, 4, and 5 of the 

Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 737–53– 

1287, Revision 1, dated November 15, 2010, 

except as required by paragraphs (i)(2) and 

(i)(3) of this AD. Repeat the applicable 

inspections thereafter at the applicable times 

specified in tables 1 through 9, paragraph 

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

Attention Service Bulletin 737–53–1287, 

Revision 1, dated November 15, 2010, until 

the actions required by paragraph (j) of this 

AD are done. 

(h) Repair 

(1) If any crack or corrosion is found 

during any inspection required by paragraph 

(g) of this AD: Repair before further flight, in 

accordance with the Accomplishment 

Instructions of Boeing Special Attention 

Service Bulletin 737–53–1287, Revision 1, 

dated November 15, 2010, except as required 

by paragraphs (i)(2) and (i)(3) of this AD. 

Repair of any crack or corrosion terminates 

the repetitive inspection requirements of 

paragraph (g) of this AD for the repaired area 

only. 

(2) Operators must obtain an approved 

damage tolerance evaluation for any repair 

installed to comply with Section 

121.1109(c)(2) or 129.109(c)(2) of the Code of 

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

or 129.109(c)(2)). 

Note 1 to paragraph (h)(2) of this AD: 

Additional guidance on damage tolerance 

evaluation for repairs can be found in table 

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

Boeing Special Attention Service Bulletin 

737–53–1287, Revision 1, dated November 

15, 2010; and Part 8 of the Accomplishment 

Instructions of Boeing Special Attention 

Service Bulletin 737–53–1287, Revision 1, 

dated November 15, 2010. 

(i) Exceptions 

(1) Where Boeing Special Attention Service 

Bulletin 737–53–1287, Revision 1, dated 

November 15, 2010, specifies a compliance 

time ‘‘after the original issue date of this 

service bulletin:’’ this AD requires 

compliance within the specified compliance 

time after the effective date of this AD. 

(2) Where Boeing Special Attention Service 

Bulletin 737–53–1287, Revision 1, dated 

November 15, 2010, specifies contacting 

Boeing for inspection or repair instructions: 

Do the applicable action using a method 

approved in accordance with the procedures 

specified in paragraph (m) of this AD. 

(3) For Group 7 airplanes, as identified in 

paragraph 1.A., ‘‘Effectivity,’’ of Boeing 

Special Attention Service Bulletin 737–53– 

1287, Revision 1, dated November 15, 2010: 

Use the applicable instructions for Group 2, 

Configuration 1, 2, or 3, as identified in 

Boeing Special Attention Service Bulletin 

737–53–1287, Revision 1, dated November 

15, 2010. 

(j) Optional Terminating Action 

For Groups 1, 2, 3, 4, 6, and 7 airplanes, 

as identified in Boeing Special Attention 

Service Bulletin 737–53–1287, Revision 1, 

dated November 15, 2010: Except as 

provided by paragraphs (i)(2) and (i)(3) of 

this AD, accomplishment of the preventive 

modification, including all applicable HFEC 

and detailed inspections for cracking or 

corrosion inside or outside the repair skin 

cutout area, in the frame fastener holes, or in 

the support channel; and all applicable 

repairs or replacements; as specified in the 

Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 737–53– 

1287, Revision 1, dated November 15, 2010: 

Terminates the repetitive inspection 

requirements of paragraph (g) of this AD. 

(k) Concurrent Skin Panel Replacement 

For Groups 2 and 7 airplanes, as identified 

in Boeing Special Attention Service Bulletin 

737–53–1287, Revision 1, dated November 

15, 2010: Before or concurrently with 

accomplishing the requirements of paragraph 

(g) of this AD, do the replacement of the 

bonded skin panels with solid skin panels, in 

accordance with the Accomplishment 

Instructions of Boeing Service Bulletin 737– 

53A1042, Revision 9, dated July 25, 1991; 

except as required by paragraph (i)(3) of this 

AD. The actions specified in paragraph (k) of 

this AD are also required by AD 90–06–02, 

Amendment 39–6489 (55 FR 8372, March 7, 

1990). 

(l) Credit for Previous Actions 

(1) This paragraph gives credit for the 

replacement required by paragraph (k) of this 

AD, if the replacement of bonded skin panels 

with solid skin panels was accomplished 

before the effective date of this AD using the 

Accomplishment Instructions of the service 

information identified in paragraphs (l)(1)(i), 

(l)(1)(ii), (l)(1)(iii), and (l)(1)(iv) of this AD: 

(i) Boeing Service Bulletin 737–53A1042 

Revision 5, dated October 5, 1984. 

(ii) Boeing Service Bulletin 737–53A1042 

Revision 6, dated August 10, 1989. 

(iii) Boeing Service Bulletin 737–53A1042 

Revision 7, dated October 19, 1989. 

(iv) Boeing Service Bulletin 737–53A1042 

Revision 8, dated July 19, 1990. 

(2) This paragraph gives credit for the 

inspections required by paragraph (g) of this 

AD, if the inspections were accomplished 

before the effective date of this AD using the 

Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 737–53– 

1287, dated March 11, 2009. 

(m) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle Aircraft 

Certification Office (ACO), FAA, has the 

authority to approve AMOCs for this AD, if 

requested using the procedures found in 14 

CFR 39.19. In accordance with 14 CFR 39.19, 

send your request to your principal inspector 

or local Flight Standards District Office, as 

appropriate. If sending information directly 

to the manager of the ACO, send it to the 

attention of the person identified in the 

Related Information section of this AD. 

Information may be emailed to 9-ANMSeattle-ACO-AMOC-Requests@faa.gov. 

(2) Before using any approved AMOC, 

notify your Principal Maintenance Inspector 

or Principal Avionics Inspector, as 

appropriate, or lacking a principal inspector, 

your local Flight Standards District Office. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any repair 

required by this AD if it is approved by the 

Boeing Commercial Airplanes Organization 

Designation Authorization (ODA) that has 

been authorized by the Manager, Seattle ACO 

to make those findings. For a repair method 

to be approved, the repair must meet the 

certification basis of the airplane, and the 

approval must specifically refer to this AD. 

(n) Related Information 

(1) For more information about this AD, 

contact Wayne Lockett, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, Seattle 

ACO, 1601 Lind Avenue SW., Renton, 

Washington 98057–3356; phone: 425–917– 

6447; fax: 425–917–6590; email: 

wayne.lockett@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 


tkelley on DSK3SPTVN1PROD with PROPOSALS
15644 Federal Register / Vol. 77, No. 52 / Friday, March 16, 2012 / Proposed Rules 

availability of this material at the FAA, call 

425–227–1221. 

Issued in Renton, Washington, on March 1, 

2012. 

Jeffrey E. Duven, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2012–6470 Filed 3–15–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0192; Directorate 

Identifier 2011–NM–225–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 certain 

Airbus Model A330–200 and –200 

freighter series airplanes; and Model 

A340–200, –300, –500, and –600 series 

airplanes. This proposed AD was 

prompted by fuel system reviews 

conducted by the manufacturer. This 

proposed AD would require 

modification of the control circuit for 

the fuel pumps for the center fuel tanks 

for certain airplanes, and center and rear 

fuel tanks for certain other airplanes. 

We are proposing this AD to prevent the 

potential of ignition sources inside fuel 

tanks, which, in combination with 

flammable fuel vapors, could result in 

fuel tank explosions and consequent 

loss of the airplane. 

DATES: We must receive comments on 

this proposed AD by April 30, 2012. 

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 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, 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 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: 

Vladimir Ulyanov, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, 

Washington 98057–3356; telephone 

425–227–1138; 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–2012–0192; Directorate Identifier 

2011–NM–225–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 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 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA 

Airworthiness Directive 2011–0196, 

dated October 7, 2011 (referred to after 

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

condition for the specified products. 

The MCAI states: 

* * * [T]he FAA issued a set of new rules 

related to Fuel Tank Safety including Special 

Federal Aviation Regulation (SFAR) 88. In 

line with SFAR88, the JAA [Joint Aviation 

Authorities] issued policy JAA INT/POL 25/ 

12 and recommended to the National 

Aviation Authorities (NAA) the application 

of a similar regulation. 

To ensure compliance with the 

requirements set by SFAR88 and JAA INT/ 

POL 25/12, this [EASA] AD requires that 

Ground Fault Interrupters (GFI) are installed 

into the electrical power supply circuits of 

fuel pumps for which the canisters become 

uncovered during normal operation, taking 

into account normal fuel reserve or the fuel 

level, triggering the low fuel level warning. 

The function of this additional system 

protection is to electrically isolate the pump 

if a ground fault condition occurs 

downstream of the GFI. The GFI gives 

additional earth leakage protection to the 

downstream circuit. 

The unsafe condition is the potential of 

ignition sources inside fuel tanks, 

which, in combination with flammable 

fuel vapors, could result in fuel tank 

explosions and consequent loss of the 

airplane. The corrective action is 

modifying the control circuits of the fuel 

pump for the rear and center fuel tanks. 

You may obtain further information by 

examining the MCAI in the AD docket. 

The FAA has examined the 

underlying safety issues involved in fuel 

tank explosions on several large 

transport airplanes, including the 

adequacy of existing regulations, the 

service history of airplanes subject to 

those regulations, and existing 

maintenance practices for fuel tank 

systems. As a result of those findings, 

we issued a regulation titled ‘‘Transport 

Airplane Fuel Tank System Design 

Review, Flammability Reduction and 

Maintenance and Inspection 

Requirements’’ (66 FR 23086, May 7, 

2001). In addition to new airworthiness 

standards for transport airplanes and 

new maintenance requirements, this 

rule included Special Federal Aviation 

Regulation No. 88 (‘‘SFAR 88,’’ 

Amendment 21–78, and subsequent 

Amendments 21–82 and 21–83). 

Among other actions, SFAR 88 (66 FR 

23086, May 7, 2001) requires certain 

type design (i.e., type certificate (TC) 

and supplemental type certificate (STC)) 

holders to substantiate that their fuel 

tank systems can prevent ignition 

sources in the fuel tanks. This 

requirement applies to type design 

holders for large turbine-powered 

transport airplanes and for subsequent 

modifications to those airplanes. It 

requires them to perform design reviews 


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