39188 Federal Register / Vol. 77, No. 127 / Monday, July 2, 2012 / Proposed Rules 

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 AD: 

Airbus: Docket No. FAA–2012–0676; 

Directorate Identifier 2011–NM–182–AD. 

(a) Comments Due Date 

We must receive comments by August 16, 

2012. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to all Airbus Model A318– 

111, –112, –121, and –122 airplanes; Model 

A319–111, –112, –113, –114, –115, –131, 

–132, and –133 airplanes; Model A320–111, 

–211, –212, –214, –231, –232, and –233 

airplanes; and Model A321–111, –112, –131, 

–211, –212, –213, –231, and –232 airplanes; 

certificated in any category; all manufacturer 

serial numbers. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 25: Equipment/Furnishings. 

(e) Reason 

This AD was prompted by reports of the 

escape slide of the raft inflation system not 

deploying when activated due to the rotation 

of the cable guide in a direction which 

resulted in jamming of the inflation control 

table. We are issuing this AD to prevent nondeployment of the inflation system of the 

escape slide raft, which could result in 

delayed evacuation from the airplane during 

an emergency, and consequent injury to the 

passengers. 

(f) Compliance 

You are responsible for having the actions 

required by this AD performed within the 

compliance times specified, unless the 

actions have already been done. 

(g) Modification 

Except as provided by paragraph (i) of this 

AD, within 36 months after the effective date 

of this AD: Modify the escape slide rafts that 

have a part number specified in table 1 of 

this AD, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–25–1723, dated 

December 17, 2010 (for Model A319, A320, 

and A321 series airplanes); or Airbus Service 

Bulletin A320–25–1724, dated December 17, 

2010 (for Model A318 series airplanes). 

TABLE 1—ESCAPE SLIDE RAFTS

Air Cruisers and Aerazur Escape Slide 

Rafts Part Number if Fitted With a Reservoir and Valve Assembly P/N D18309– 

105 or P/N D18309–205 

D30664–105 

D30664–107 

TABLE 1—ESCAPE SLIDE RAFTS— 

Continued 

D30664–109 

D30664–305 

D30664–307 

D30664–309 

D30664–311 

D30665–105 

D30665–107 

D30665–109 

D30665–305 

D30665–307 

D30665–309 

D30665–311 

(h) Replacement in Accordance With Air 

Cruisers Service Bulletin 

Replacement of all affected escape slide 

rafts on any affected airplane with slide rafts 

that have been modified in accordance with 

the Accomplishment Instructions of Air 

Cruisers Service Bulletin S.B. A320 004–25– 

85, dated November 30, 2010, is acceptable 

for compliance with the requirements of 

paragraph (g) of this AD. 

(i) Airplanes Not Affected by Paragraph (g) 

This AD 

Airplanes on which Airbus modification 

151459 or modification 151502 has been 

embodied in production, and on which no 

escape slide raft replacements have been 

made since first flight, are not affected by the 

requirement specified in paragraph (g) of this 

AD. 

(j) Parts Installation 

(1) For airplanes other than those 

identified in paragraph (i) of this AD: After 

accomplishment of the modification required 

by paragraph (g) of this AD or after 

accomplishment the replacement specified in 

paragraph (h) of this AD, no person may 

install, on any airplane, an escape slide raft 

specified in table 1 of this AD, unless it has 

been modified in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–25–1723, dated 

December 17, 2010 (for Model A319, A320, 

and A321 series airplanes); Airbus Service 

Bulletin A320–25–1724, dated December 17, 

2010 (for Model A318 series airplanes); or 

Air Cruisers Service Bulletin A320 004–25– 

85, dated November 30, 2010 (for Model 

A318, A319, A320, and A321 series 

airplanes). 

(2) For airplanes identified in paragraph (i) 

of this AD: As the effective date of this AD, 

no person may install, on any airplane, an 

escape slide raft specified in table 1 of this 

AD, unless it has been modified in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A320– 

25–1723, dated December 17, 2010 (for 

Model A319, A320, and A321 series 

airplanes); Airbus Service Bulletin A320–25– 

1724, dated December 17, 2010 (for Model 

A318 series airplanes); or Air Cruisers 

Service Bulletin A320 004–25–85, dated 

November 30, 2010 (for Model A318, A319, 

A320, and A321 series airplanes). 

(k) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, 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 International Branch, send it to ATTN: 

Sanjay Ralhan, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, Washington 98057– 

3356; telephone (425) 227–1405; fax (425) 

227–1149. Information may be emailed to: 9– 

ANM–116–AMOC–REQUESTS@faa.gov. 

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. The AMOC 

approval letter must specifically reference 

this AD. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

(l) Related Information 

Refer to MCAI EASA Airworthiness 

Directive 2011–0160, dated August 26, 2011; 

and the service information specified in 

paragraphs (1)(1) through (1)(3) of this AD; 

for related information. 

(1) Airbus Service Bulletin A320–25–1723, 

dated December 17, 2010. 

(2) Airbus Service Bulletin A320–25–1724, 

dated December 17, 2010. 

(3) Air Cruisers Service Bulletin A320 004– 

25–85, dated November 30, 2010. 

Issued in Renton, Washington, on June 26, 

2012. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2012–16096 Filed 6–29–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–1160; Directorate 

Identifier 2010–NM–148–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. 


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SUMMARY: We are revising an earlier 

proposed airworthiness directive (AD) 

to supersede an existing AD for all The 

Boeing Company Model 767 airplanes. 

The existing AD currently requires 

repetitive inspections to detect 

discrepancies of the wiring and 

surrounding Teflon sleeves of the fuel 

tank boost pumps and override/jettison 

pumps; replacement of the sleeves with 

new sleeves, for certain airplanes; and 

repair or replacement of the wiring and 

sleeves with new parts, as necessary. 

The previous NPRM proposed to reduce 

the initial compliance time and 

repetitive inspection interval in the 

existing AD. The previous NPRM was 

prompted by fleet information 

indicating that the repetitive inspection 

interval in the existing AD is too long 

because excessive chafing of the 

sleeving continues to occur much earlier 

than expected between scheduled 

inspections. This action revises the 

previous NPRM by proposing a 

terminating action for the repetitive 

inspections, to eliminate wire damage. 

This action also removes certain 

airplanes from the applicability of the 

previous NPRM. We are proposing this 

supplemental NPRM to detect and 

correct chafing of the fuel pump wire 

insulation and consequent exposure of 

the electrical conductor, which could 

result in electrical arcing between the 

wires and conduit and consequent fire 

or explosion of the fuel tank. 

Since these actions impose an 

additional burden over that proposed in 

the previous 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 August 16, 

2012. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, by any of the following 

methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC 20590. 

• Hand Delivery: 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; 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: 

Rebel Nichols, Aerospace Engineer, 

Propulsion Branch, ANM–140S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue SW., Renton, 

Washington 98057–3356; phone: 425– 

917–6509; fax: 425–917–6590; email: 

rebel.nichols@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–2010–1160; Directorate Identifier 

2010–NM–148–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 supersede AD 2000–11–06, 

Amendment 39–11754 (65 FR 34928, 

June 1, 2000; corrected August 1, 2000 

(65 FR 46862)), that would apply to all 

Model 767–200, –300, –300F, and 

–400ER series airplanes. That NPRM 

published in the Federal Register on 

December 14, 2010 (75 FR 77790). The 

existing AD currently requires repetitive 

inspections to detect discrepancies of 

the wiring and surrounding Teflon 

sleeves of the fuel tank boost pumps and 

override/jettison pumps; replacement of 

the sleeves with new sleeves, for certain 

airplanes; and repair or replacement of 

the wiring and sleeves with new parts, 

as necessary. That NPRM proposed to 

reduce the initial compliance time and 

repetitive inspection interval in the 

existing AD. 

Actions Since Previous NPRM (75 FR 

77790, December 14, 2010) Was Issued 

Since we issued the previous NPRM 

(75 FR 77790, December 14, 2010), the 

manufacturer has issued Boeing Alert 

Service Bulletin 767–28A0104, Revision 

1, dated March 2, 2012, to replace the 

fuel boost pump and override/jettison 

pump wire bundles inside the in-tank 

conduits with new wire bundles. The 

new wire bundles have liners which 

hold the fuel pump power wires away 

from the sides of the metal conduit, to 

eliminate chafing. Boeing Alert Service 

Bulletin 767–28A0104, Revision 1, 

dated March 2, 2012, also removes 

certain airplanes from the effectivity. 

Comments 

We gave the public the opportunity to 

comment on the previous NPRM (75 FR 

77790, December 14, 2010). The 

following presents the comments 

received on the previous NPRM and the 

FAA’s response to each comment. 

Request To Delay Issuance of the 

Previous NPRM (75 FR 77790, 

December 14, 2010) 

Continental Airlines (CAL) asked that 

we delay issuance of the previous 

NPRM (75 FR 77790, December 14, 

2010) until Boeing Alert Service 

Bulletin 767–28A0104, dated January 

25, 2011, is revised to include a change 

to the airplane fuel boost pump and 

override jettison pump wiring. CAL 

stated that it was informed that the 

revised bulletin was currently in the 

approval process. CAL noted that, in 

accordance with Boeing Alert Service 

Bulletin 767–28A0104, dated January 

25, 2011, paragraph (e) of the previous 

NPRM provides the information 

regarding the unsafe condition and 

reduction of repetitive inspection 

intervals. CAL also stated that, although 

these repetitive inspection intervals may 

detect and correct chafing of the fuel 

pump wire insulation and consequent 

exposure of the electrical conductor, 


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which could result in an unsafe 

condition, the following issues are 

created by the service information 

referenced in the previous NPRM: 

• Does not provide requirements of 

system design changes to permanently 

eliminate the unsafe condition. 

• Does impose operational and 

logistical difficulties to operator with 

the scheduling of the short repetitive 

inspection intervals. 

• Does impose additional economic 

burden to operator with the repetitive 

maintenance inspection requirements in 

lieu of one-time low cost terminating 

action. 

We do not agree to delay issuing the 

supplemental NPRM because the 

proposed actions are required to address 

the unsafe condition. However, we do 

agree that the revised service 

information should be included in this 

supplemental NPRM. As explained 

previously, Boeing has issued Alert 

Service Bulletin 767–28A0104, Revision 

1, dated March 2, 2012. That service 

bulletin includes procedures for a 

wiring change to the fuel boost pump 

and override/jettison pump. We 

reviewed that service bulletin and have 

included it in a new terminating action 

specified in paragraph (l) of this 

supplemental NPRM. 

Requests To Clarify Applicability 

Boeing asked that we revise the 

applicability identified in the previous 

NPRM (75 FR 77790, December 14, 

2010) to include specific airplane 

effectivities. Boeing stated that 

production-certified changes 

implemented at line number 990 and on 

constituted terminating action against 

inspection requirements of the Teflon 

sleeves around the wiring. Boeing noted 

that the service information referenced 

in the previous NPRM is being revised 

to limit the airplane effectivity up to 

and including line number 989. CAL 

stated that, in the Boeing 767 Airplane 

Maintenance Manual there are two fuel 

pump wire installation configurations 

for the Model 767 fleet. CAL added that 

the previous NPRM does not provide a 

specific clarification as to which 

airplane configuration the regulatory 

requirements apply, other than the 

effectivity of Boeing Alert Service 

Bulletin 767–28A0053, Revision 2, 

dated June 24, 2010. 

We agree that the applicability (all 

Model 767–200, –300, –300F, and 

–400ER series airplanes) specified in the 

previous NPRM (75 FR 77790, 

December 14, 2010) should be clarified, 

and have determined that not all 

airplanes are affected. Boeing has issued 

Service Bulletin 767–28A0053, Revision 

3, dated November 11, 2011. Boeing 

Service Bulletin 767–28A0053, Revision 

1, dated August 5, 1999; and Boeing 

Alert Service Bulletin 767–28A0053, 

Revision 2, dated June 24, 2010; were 

referred to as the sources of service 

information for accomplishing certain 

actions in the previous NPRM. Revision 

3 of Boeing Service Bulletin 767– 

28A0053, dated November 11, 2011, 

specifies no more work is necessary on 

airplanes changed in accordance with 

Boeing Service Bulletin 767–28A0053, 

Revision 1, dated August 5, 1999; or 

Boeing Alert Service Bulletin 767– 

28A0053, Revision 2, dated June 24, 

2010. Boeing Service Bulletin 767– 

28A0053, Revision 3, dated November 

11, 2011, clarifies the effectivity and 

certain procedures in the 

Accomplishment Instructions, and 

removes the optional fuel pump check. 

We have added Boeing Service Bulletin 

767–28A0053, Revision 3, dated 

November 11, 2011, as a source of 

service information for accomplishing 

the required actions in this 

supplemental NPRM. We have also 

changed the applicability in this 

supplemental NPRM from ‘‘all’’ to ‘‘as 

identified in Boeing Service Bulletin 

767–28A0053, Revision 3, dated 

November 11, 2011.’’ 

Requests To Include Information Notice 

United Airlines (UAL) asked that we 

include Boeing Service Bulletin 

Information Notice 767–28A0053 IN05, 

dated August 12, 2010, in the previous 

NPRM (75 FR 77790, December 14, 

2010). UAL stated that this information 

notice informs operators that Boeing 

Alert Service Bulletin 767–28A0053, 

Revision 2, dated June 24, 2010, will be 

revised to provide optional connector 

part numbers and delete the optional 

fuel pump check. UAL noted that this 

would allow operators to use the 

information notice without the need to 

request an alternative method of 

compliance (AMOC). All Nippon 

Airways also asked that we allow the 

use of optional connectors. 

As noted above, Boeing has issued 

Service Bulletin 767–28A0053, Revision 

3, dated November 11, 2011. Boeing 

Service Bulletin 767–28A0053, Revision 

3, dated November 11, 2011, 

incorporates the changes in Boeing 

Service Bulletin Information Notice 

767–28A0053 IN05, dated August 12, 

2010, into the Accomplishment 

Instructions. Therefore, no change to 

this supplemental NPRM is necessary in 

this regard. 

Request To Include Terminating Action 

UAL asked that terminating action for 

the repetitive inspections be added to 

the previous NPRM (75 FR 77790, 

December 14, 2010). UAL noted that 

Boeing may be developing a solution 

that would terminate the inspections 

proposed by the previous NPRM. 

As noted above, Boeing has issued 

Alert Service Bulletin 767–28A0104, 

Revision 1, dated March 2, 2012. Boeing 

Alert Service Bulletin 767–28A0104, 

Revision 1, dated March 2, 2012, adds 

replacement of the fuel boost pump and 

override/jettison pump wire bundles 

with new wire bundles; which 

eliminates the need for the repetitive 

inspections. We have added a new 

paragraph (l) to this supplemental 

NPRM to include that terminating 

action. 

Requests To Clarify Certain 

Requirement 

American Airlines (AAL) asked for 

clarification on the following items: 

• Paragraph (g) of the previous NPRM 

(75 FR 77790, December 14, 2010) used 

the word ‘‘splice’’ in the examples of 

discrepancies; however, AAL noted that 

the referenced service bulletin does not 

use the word ‘‘splice’’ and it is not 

aware of any practical methods to splice 

Teflon. AAL did not ask for a change. 

• Paragraphs (h) and (i) of the 

previous NPRM (75 FR 77790, 

December 14, 2010) refer to paragraph 

D. of the Accomplishment Instructions 

of Boeing Alert Service Bulletin 767– 

28A0053, Revision 2, dated June 24, 

2010. This reference is correct in Boeing 

Service Bulletin 767–28A0053, Revision 

1, dated August 5, 1999, but is incorrect 

in Boeing Alert Service Bulletin 767– 

28A0053, Revision 2, dated June 24, 

2010, because the numbering scheme in 

the revised service information has 

changed. 

• Paragraph (i)(2)(ii) of the previous 

NPRM (75 FR 77790, December 14, 

2010) refers to ‘‘paragraph (a) of this 

AD.’’ However, this reference should be 

changed to paragraph (g) of this AD 

because the numbering scheme of the 

previous NPRM has changed from that 

specified in the existing AD. 

• Paragraph (j) of the previous NPRM 

(75 FR 77790, December 14, 2010) refers 

to paragraphs G., H., I., or J. of Boeing 

Service Bulletin 767–28A0053, Revision 

1, dated August 5, 1999, but omits 

references to Boeing Alert Service 

Bulletin 767–28A0053, Revision 2, 

dated June 24, 2010. 

We agree with the commenter’s 

concerns and offer the following 

clarifications: 

• We have removed the word 

‘‘splices’’ from paragraph (g) of this 

supplemental NPRM for clarity. 

• We have removed the specific 

reference to ‘‘paragraph D.’’ of the 

Accomplishment Instructions from 


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paragraphs (h) and (i) of this 

supplemental NPRM for clarity. 

• We have changed the reference to 

paragraph (a) in paragraph (i)(2)(ii) of 

the previous NPRM (75 FR 77790, 

December 14, 2010) to paragraph (g) in 

this supplemental NPRM to refer to the 

correct paragraph identifier. 

• We have removed the reference to 

paragraphs G., H., I., or J. in paragraph 

(j) of this supplemental NPRM, since 

there are three versions of the service 

bulletin. We have included references to 

Boeing Alert Service Bulletin 767– 

28A0053, Revision 2, dated June 24, 

2010; and Boeing Service Bulletin 767– 

28A0053, Revision 3, dated November 

11, 2011; in paragraph (j) of this 

supplemental NPRM. 

UAL also asked that paragraphs (h) 

and (i) of the previous NPRM (75 FR 

77790, December 14, 2010) be revised 

for clarification. UAL stated that those 

paragraphs refer to paragraph D. of the 

Accomplishment Instructions of Boeing 

Alert Service Bulletin 767–28A0053, 

Revision 2, dated June 24, 2010, and 

there is no paragraph D. in Revision 2 

of that service bulletin. UAL asked that 

we change those paragraphs for 

clarification. In addition, UAL asked 

that we refer to Boeing Alert Service 

Bulletin 767–28A0053, Revision 2, 

dated June 24, 2010; or Revision 3, 

dated November 11, 2011; in paragraph 

(j) of the previous NPRM. 

As noted above, we agree and have 

removed the specific reference to 

‘‘paragraph D.’’ of the Accomplishment 

Instructions of Boeing Alert Service 

Bulletin 767–28A0053, Revision 2, 

dated June 24, 2010, from paragraphs (h) 

and (i) of this supplemental NPRM. We 

also revised paragraph (j) of this 

supplemental NPRM to refer to Boeing 

Alert Service Bulletin 767–28A0053, 

Revision 2, dated June 24, 2010; or 

Revision 3, dated November 11, 2011. 

Request To Remove Reporting 

Requirement 

AAL asked that the reporting 

requirement in paragraph (k) of the 

previous NPRM (75 FR 77790, 

December 14, 2010) be removed. AAL 

stated that paragraph (k) of the previous 

NPRM contains the following language, 

‘‘Submit a report of positive inspection 

findings (findings of discrepancies 

only), along with any damaged wiring 

and sleeves, to the Seattle 

Manufacturing Inspection District Office 

(MIDO) * * *’’ AAL noted that this 

statement is identical to paragraph (e) of 

the existing AD, and added that any 

additional damaged wiring and sleeving 

reports sent to the FAA in Seattle would 

not have an appreciable benefit in 

finding a solution to the chafing 

problem. AAL asked that this paragraph 

be removed, or if not removed, extended 

due to the nature of the inspections and 

the ability to report any damaged wiring 

and sleeving within the 10-day 

compliance time. 

We agree with the commenter because 

the benefit of reporting after so many 

years is minimal. The data necessary for 

determining a permanent fix for the 

wiring has been compiled, and there is 

a terminating modification for the 

wiring specified in paragraph (l) of this 

supplemental NPRM. Therefore, we 

have removed paragraph (k) of the 

previous NPRM (75 FR 77790, 

December 14, 2010), and the related 

paperwork reduction act language in 

paragraph (m) of the previous NPRM, 

and reidentified subsequent paragraphs 

in this supplemental NPRM 

accordingly. 

Request To Restate Incorporation by 

Reference and Special Flight Permit 

Paragraphs 

AAL noted the absence of the Special 

Flight Permits and Incorporation by 

Reference paragraphs, in paragraphs (g) 

and (h) of the existing AD, and asked 

that those paragraphs be restated in the 

previous NPRM (75 FR 77790, 

December 14, 2010). 

We acknowledge the commenter’s 

concerns. However, the Special Flight 

Permits paragraph specified in the 

existing AD has now been removed from 

all ADs because that information is 

contained in sections 21.197 and 21.199 

of the Federal Aviation Regulations (14 

CFR 21.197 and 21.199). The 

Incorporation by Reference section of an 

AD is only included in final rules to 

incorporate the required service 

information. Therefore, those 

paragraphs are not restated in this 

supplemental NPRM. 

Request To Include Alternative 

Methods of Compliance 

CAL and UAL asked that Boeing 

Service Bulletins 767–28A0079 and 

767–28A0080, which have been 

approved by the Seattle Aircraft 

Certification Office (ACO) as an AMOC 

to AD 2000–11–06, Amendment 39– 

11754 (65 FR 34928, June 1, 2000; 

corrected August 1, 2000 (65 FR 

46862)), be approved as an AMOC for 

the corresponding requirements in the 

previous NPRM (75 FR 77790, 

December 14, 2010). 

All Nippon Airways noted that its 

AMOC, Letter 140S–10–385, dated 

October 21, 2010, is also approved by 

the Seattle ACO as an AMOC to AD 

2000–11–06, Amendment 39–11754 (65 

FR 34928, June 1, 2000; corrected 

August 1, 2000 (65 FR 46862)). We infer 

that All Nippon Airways is asking that 

the letter be approved as an AMOC for 

the corresponding requirements in the 

previous NPRM (75 FR 77790, 

December 14, 2010). 

We agree with the commenters’ 

requests. Paragraph (n)(3) of this 

supplemental NPRM includes 

previously approved AMOCs to AD 

2000–11–06, Amendment 39–11754 (65 

FR 34928, June 1, 2000; corrected 

August 1, 2000 (65 FR 46862)), as 

AMOCs with the corresponding 

requirements of this supplemental 

NPRM. The terminating action and 

reduced inspection intervals in this 

supplemental NPRM have no 

corresponding action in AD 2000–11– 

06. Therefore, no change to the 

supplemental NPRM is necessary in this 

regard. 

Request To Change Compliance Time 

UAL asked that the compliance time 

for certain inspections specified in the 

previous NPRM (75 FR 77790, 

December 14, 2010) be changed. UAL 

stated that paragraph (l)(1) of the 

previous NPRM requires inspecting 

within 15,000 flight hours after the most 

recent inspection or within 6,000 flight 

hours after the effective date of the AD, 

whichever occurs later, but not to 

exceed 60,000 flight hours after the most 

recent inspection required by paragraph 

(g) of the previous NPRM. UAL 

suggested that the compliance time be 

changed to within 60,000 flight hours or 

30,000 flight cycles after the effective 

date of the AD, whichever occurs first. 

We do not agree with the commenter. 

In developing an appropriate 

compliance time for the inspections, we 

considered not only the degree of 

urgency associated with addressing the 

subject unsafe condition, but the 

manufacturer’s recommendation for an 

appropriate compliance time, and the 

practical aspect of accomplishing the 

required inspections within a period of 

time that corresponds to the normal 

scheduled maintenance for most 

affected operators. However, under the 

provisions of paragraph (n) of this 

supplemental NPRM, we will consider 

requests for approval of a change to the 

compliance time if sufficient data are 

submitted to substantiate that the new 

compliance time would provide an 

acceptable level of safety. No change to 

this supplemental NPRM is necessary in 

this regard. 

Request To Increase Work-Hours in 

Costs of Compliance 

UAL asked that we increase the 

number of work-hours specified in the 

previous NPRM (75 FR 77790, 

December 14, 2010) for the actions done 


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on airplanes with and without jettison 

pumps. UAL stated that Boeing Alert 

Service Bulletin 767–28A0053, Revision 

2, dated June 24, 2010, specifies 6.5 

work-hours to do the actions for 

airplanes with jettison pumps, and 5.25 

work-hours to do the actions for 

airplanes without jettison pumps. 

We agree with the commenter for the 

reasons provided. We have increased 

the number of work-hours for those 

airplanes in the Costs of Compliance 

section of this supplemental NPRM 

accordingly. 

Changes to Supplemental NPRM 

We have added a new paragraph (m) 

to this supplemental NPRM to provide 

credit for actions performed before the 

effective date of the AD using Boeing 

Service Bulletin 767–28A0104, dated 

January 25, 2011. 

We have removed Note 1 of the 

previous NPRM (75 FR 77790, 

December 14, 2010). 

We have revised certain headings 

throughout this supplemental NPRM. 

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 the same type 

design. Certain changes described above 

expand the scope of the previous NPRM 

(75 FR 77790, December 14, 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 service information 

described previously. 

Costs of Compliance 

We estimate that this proposed AD 

affects 414 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 

Actions for airplanes with jettison pumps, required by AD 2000–11–06, Amendment 

39–11754 (65 FR 34928, June 1, 2000; 

corrected August 1, 2000 (65 FR 46862)).

7 work-hours × $85 

per hour = $595 per 

inspection cycle.

None .......................... $595 per inspection 

cycle.

Up to $246,330 per inspection cycle. 

Actions for airplanes without jettison pumps, 

required by AD 2000–11–06, Amendment 

39–11754 (65 FR 34928, June 1, 2000; 

corrected August 1, 2000 (65 FR 46862)).

5 work-hours × $85 

per hour = $425 per 

inspection cycle.

None .......................... $425 per inspection 

cycle.

Up to $175,950 per inspection cycle. 

New proposed action: Replace existing wire 

bundles with new wire bundles.

33 work hours × $85 

per hour = $2,805.

$6,061 ........................ $8,866 ........................ $3,670,524 

We estimate the following costs to do 

any necessary repairs that would be 

required based on the results of the 

inspections. We have no way of 

determining the number of aircraft that 

might need these repairs: 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per 

product 

Replace wire bundle sleeves if damage found during inspections.1 work hour × $85 per hour = $85 .................................. $1,452 $1,537 

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: 


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PART 39—AIRWORTHINESS 

DIRECTIVES 

1. The authority citation for part 39 

continues to read as follows: 

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

§ 39.13 [Amended] 

2. The FAA amends § 39.13 by 

removing airworthiness directive (AD) 

2000–11–06, Amendment 39–11754 (65 

FR 34928, June 1, 2000; corrected 

August 1, 2000 (65 FR 46862)), and 

adding the following new AD: 

The Boeing Company: Docket No. FAA– 

2010–1160; Directorate Identifier 2010– 

NM–148–AD. 

(a) Comments Due Date 

We must receive comments by August 16, 

2012. 

(b) Affected ADs 

This AD supersedes AD 2000–11–06, 

Amendment 39–11754 (65 FR 34928, June 1, 

2000; corrected August 1, 2000 (65 FR 

46862)). 

(c) Applicability 

This AD applies to The Boeing Company 

Model 767–200, –300, –300F, and –400ER 

series airplanes; certificated in any category; 

as identified in Boeing Service Bulletin 767– 

28A0053, Revision 3, dated November 11, 

2011. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 28: Fuel. 

(e) Unsafe Condition 

This AD was prompted by fleet 

information indicating that the repetitive 

inspection interval in the existing AD is too 

long because excessive chafing of the 

sleeving continues to occur much earlier than 

expected between scheduled inspections. We 

are issuing this AD to detect and correct 

chafing of the fuel pump wire insulation and 

consequent exposure of the electrical 

conductor, which could result in electrical 

arcing between the wires and conduit and 

consequent fire or explosion of the fuel tank. 

(f) Compliance 

You are responsible for having the actions 

required by this AD performed within the 

compliance times specified, unless the 

actions have already been done. 

(g) Retained Repetitive Inspections 

This paragraph restates the requirements of 

paragraph (a) of AD 2000–11–06, 

Amendment 39–11754 (65 FR 34928, June 1, 

2000; corrected August 1, 2000 (65 FR 

46862)), with revised service information. 

Perform a detailed visual inspection to detect 

discrepancies—including the presence of 

cuts, splits, holes, worn areas, and lacing ties 

installed on the outside of the sleeves (except 

at the sleeve ends)—of the Teflon sleeves 

surrounding the wiring of the fuel tank boost 

pumps and override/jettison pumps, at the 

earlier of the times specified in paragraphs 

(g)(1) and (g)(2) of this AD, in accordance 

with Boeing Service Bulletin 767–28A0053, 

Revision 1, dated August 5, 1999; Boeing 

Alert Service Bulletin 767–28A0053, 

Revision 2, dated June 24, 2010; or Boeing 

Service Bulletin 767–28A0053, Revision 3, 

dated November 11, 2011. Repeat the 

inspection thereafter at intervals not to 

exceed 60,000 flight hours or 30,000 flight 

cycles, whichever occurs first. As of the 

effective date of this AD, only Boeing Alert 

Service Bulletin 767–28A0053, Revision 3, 

dated November 11, 2011, may be used to do 

the actions required by this paragraph. 

(1) Prior to the accumulation of 50,000 

total flight hours, or within 90 days after July 

6, 2000 (the effective date of AD 2000–11–06, 

Amendment 39–11754 (65 FR 34928, June 1, 

2000; corrected August 1, 2000 (65 FR 

46862)), whichever occurs later. 

(2) Within 18 months after July 6, 2000 (the 

effective date of AD 2000–11–06, 

Amendment 39–11754 (65 FR 34928, June 1, 

2000; corrected August 1, 2000 (65 FR 

46862)). 

(h) Retained Corrective Actions 

This paragraph restates the requirements of 

paragraph (b) of AD 2000–11–06, 

Amendment 39–11754 (65 FR 34928, June 1, 

2000; corrected August 1, 2000 (65 FR 

46862)), with revised service information. If 

any discrepancy is detected during any 

inspection required by paragraph (g) of this 

AD: Prior to further flight, remove the Teflon 

sleeves and perform a detailed visual 

inspection to detect damage of the wiring, in 

accordance with the Accomplishment 

Instructions of Boeing Service Bulletin 767– 

28A0053, Revision 1, dated August 5, 1999; 

Boeing Alert Service Bulletin 767–28A0053, 

Revision 2, dated June 24, 2010; or Boeing 

Service Bulletin 767–28A0053, Revision 3, 

dated November 11, 2011. As of the effective 

date of this AD, only Boeing Alert Service 

Bulletin 767–28A0053, Revision 3, dated 

November 11, 2011, may be used to do the 

actions required by this AD. 

(1) If no damage to the wiring is detected, 

prior to further flight, install new Teflon 

sleeves, in accordance with the 

Accomplishment Instructions of Boeing 

Service Bulletin 767–28A0053, Revision 1, 

dated August 5, 1999; Boeing Alert Service 

Bulletin 767–28A0053, Revision 2, dated 

June 24, 2010; or Boeing Service Bulletin 

767–28A0053, Revision 3, dated November 

11, 2011. As of the effective date of this AD, 

only Boeing Alert Service Bulletin 767– 

28A0053, Revision 3, dated November 11, 

2011, may be used to do the actions required 

by this AD. 

(2) If any damage to the wiring is detected, 

prior to further flight, accomplish the 

requirements of paragraph (i) of this AD. 

(i) Retained Corrective Actions 

This paragraph restates the requirements of 

paragraph (c) of AD 2000–11–06, 

Amendment 39–11754 (65 FR 34928, June 1, 

2000; corrected August 1, 2000 (65 FR 

46862)), with revised service information. If 

any damage to the wiring is detected during 

any inspection required by paragraph (h) of 

this AD: Prior to further flight, perform a 

detailed visual inspection to determine if the 

wiring damage was caused by arcing, in 

accordance with the Accomplishment 

Instructions of Boeing Service Bulletin 767– 

28A0053, Revision 1, dated August 5, 1999; 

Boeing Alert Service Bulletin 767–28A0053, 

Revision 2, dated June 24, 2010; or Boeing 

Service Bulletin 767–28A0053, Revision 3, 

dated November 11, 2011. As of the effective 

date of this AD, only Boeing Alert Service 

Bulletin 767–28A0053, Revision 3, dated 

November 11, 2011, may be used to do the 

actions required by this AD. 

(1) If the wire damage was not caused by 

arcing: Prior to further flight, repair any 

damaged wires or replace the wires with new 

or serviceable wires, as applicable, and 

install new Teflon sleeves, in accordance 

with the Accomplishment Instructions of 

Boeing Service Bulletin 767–28A0053, 

Revision 1, dated August 5, 1999; Boeing 

Alert Service Bulletin 767–28A0053, 

Revision 2, dated June 24, 2010; or Boeing 

Service Bulletin 767–28A0053, Revision 3, 

dated November 11, 2011. As of the effective 

date of this AD, only Boeing Alert Service 

Bulletin 767–28A0053, Revision 3, dated 

November 11, 2011, may be used to do the 

actions required by this AD. 

(2) If any damage caused by arcing is 

found: Prior to further flight, perform an 

inspection for signs of fuel inside the conduit 

or on the wires, in accordance with the 

Accomplishment Instructions of Boeing 

Service Bulletin 767–28A0053, Revision 1, 

dated August 5, 1999; Boeing Alert Service 

Bulletin 767–28A0053, Revision 2, dated 

June 24, 2010; or Boeing Service Bulletin 

767–28A0053, Revision 3, dated November 

11, 2011. As of the effective date of this AD, 

only Boeing Alert Service Bulletin 767– 

28A0053, Revision 3, dated November 11, 

2011, may be used to do the actions required 

by this AD. 

(i) If no sign of fuel is found, accomplish 

the actions specified by paragraphs 

(i)(2)(i)(A), (i)(2)(i)(B), (i)(2)(i)(C), and 

(i)(2)(i)(D) of this AD. 

(A) Prior to further flight, repair the wires 

or replace the wires with new or serviceable 

wires, as applicable, in accordance with the 

Accomplishment Instructions of Boeing 

Service Bulletin 767–28A0053, Revision 1, 

dated August 5, 1999; Boeing Alert Service 

Bulletin 767–28A0053, Revision 2, dated 

June 24, 2010; or Boeing Service Bulletin 

767–28A0053, Revision 3, dated November 

11, 2011. As of the effective date of this AD, 

only Boeing Alert Service Bulletin 767– 

28A0053, Revision 3, dated November 11, 

2011, may be used to do the actions required 

by this AD. 

(B) Prior to further flight, install new 

Teflon sleeves, in accordance with the 

Accomplishment Instructions of Boeing 

Service Bulletin 767–28A0053, Revision 1, 

dated August 5, 1999; Boeing Alert Service 

Bulletin 767–28A0053, Revision 2, dated 

June 24, 2010; or Boeing Service Bulletin 

767–28A0053, Revision 3, dated November 

11, 2011. As of the effective date of this AD, 

only Boeing Alert Service Bulletin 767– 

28A0053, Revision 3, dated November 11, 

2011, may be used to do the actions required 

by this AD. 

(C) Repeat the inspection for signs of fuel 

inside the conduit thereafter at intervals not 

to exceed 500 flight hours, until the 


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requirements of paragraph (h)(2)(i)(D) of this 

AD have been accomplished. If any fuel is 

found inside the conduit during any 

inspection required by this paragraph, prior 

to further flight, replace the conduit with a 

new or serviceable conduit in accordance 

with the Accomplishment Instructions of 

Boeing Service Bulletin 767–28A0053, 

Revision 1, dated August 5, 1999; Boeing 

Alert Service Bulletin 767–28A0053, 

Revision 2, dated June 24, 2010; or Boeing 

Service Bulletin 767–28A0053, Revision 3, 

dated November 11, 2011. Thereafter, repeat 

the inspection specified in paragraph (g) of 

this AD at intervals not to exceed 60,000 

flight hours or 30,000 flight cycles, 

whichever occurs first. As of the effective 

date of this AD, only Boeing Alert Service 

Bulletin 767–28A0053, Revision 3, dated 

November 11, 2011, may be used to do the 

actions required by this AD. 

(D) Within 6,000 flight hours or 18 months 

after the initial fuel inspection specified by 

paragraph (h)(2) of this AD, whichever occurs 

first, replace the conduit with a new or 

serviceable conduit, in accordance with the 

Accomplishment Instructions of Boeing 

Service Bulletin 767–28A0053, Revision 1, 

dated August 5, 1999; Boeing Alert Service 

Bulletin 767–28A0053, Revision 2, dated 

June 24, 2010; or Boeing Service Bulletin 

767–28A0053, Revision 3, dated November 

11, 2011. Such conduit replacement 

constitutes terminating action for the 

repetitive fuel inspections required by 

paragraph (i)(2)(i)(C) of this AD. As of the 

effective date of this AD, only Boeing Alert 

Service Bulletin 767–28A0053, Revision 3, 

dated November 11, 2011, may be used to do 

the actions required by this AD. 

(ii) If any fuel is found in the conduit or 

on any wire: Prior to further flight, replace 

the conduit with a new or serviceable 

conduit, replace damaged wires with new or 

serviceable wires, and install new Teflon 

sleeves; in accordance with the 

Accomplishment Instructions of Boeing 

Service Bulletin 767–28A0053, Revision 1, 

dated August 5, 1999; Boeing Alert Service 

Bulletin 767–28A0053, Revision 2, dated 

June 24, 2010; or Boeing Service Bulletin 

767–28A0053, Revision 3, dated November 

11, 2011. Thereafter, repeat the inspection 

specified in paragraph (g) of this AD at 

intervals not to exceed 60,000 flight hours or 

30,000 flight cycles, whichever occurs first. 

As of the effective date of this AD, only 

Boeing Alert Service Bulletin 767–28A0053, 

Revision 3, dated November 11, 2011, may be 

used to do the actions required by this AD. 

(j) Retained Pump Retest 

This paragraph restates the requirements of 

paragraph (d) of AD 2000–11–06, 

Amendment 39–11754 (65 FR 34928, June 1, 

2000; corrected August 1, 2000 (65 FR 

46862)), with revised service information. 

For any wire bundle removed and reinstalled 

during any inspection required by this AD: 

Prior to further flight after such 

reinstallation, retest the fuel pump in 

accordance with the Accomplishment 

Instructions of Boeing Service Bulletin 767– 

28A0053, Revision 1, dated August 5, 1999; 

Boeing Alert Service Bulletin 767–28A0053, 

Revision 2, dated June 24, 2010; or Boeing 

Service Bulletin 767–28A0053, Revision 3, 

dated November 11, 2011. As of the effective 

date of this AD, only Boeing Alert Service 

Bulletin 767–28A0053, Revision 3, dated 

November 11, 2011, may be used to do the 

actions required by this AD. 

(k) New Repetitive Inspections With 

Reduced Inspection Intervals 

Do the inspection required by paragraph (g) 

of this AD at the time specified in paragraph 

(l)(1) or (l)(2) of this AD, as applicable, in 

accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

767–28A0053, Revision 3, dated November 

11, 2011. Repeat the inspection thereafter at 

intervals not to exceed 15,000 flight hours. 

Accomplishing the first inspection in this 

paragraph ends the repetitive inspection 

requirements in paragraph (g) of this AD. 

(1) For airplanes on which the inspection 

required by paragraph (g) of this AD has been 

done as of the effective date of this AD: Do 

the inspection within 15,000 flight hours 

after the most recent inspection or within 

6,000 flight hours after the effective date of 

this AD, whichever occurs later; but not to 

exceed 60,000 flight hours after the most 

recent inspection required by paragraph (g) of 

this AD. 

(2) For airplanes on which the inspection 

required by paragraph (g) of this AD has not 

been done as of the effective date of this AD: 

Do the inspection before the accumulation of 

15,000 total flight hours or within 6,000 

flight hours after the effective date of this AD, 

whichever occurs later. 

(l) New Terminating Action 

Within 60 months after the effective date 

of this AD: Replace the fuel boost pump and 

override/jettison pump wire bundles inside 

the in-tank electrical conduit with new wire 

bundles, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 767–28A0104, Revision 1, 

dated March 2, 2012. Accomplishing the 

replacement specified in this paragraph ends 

the repetitive inspection requirements in 

paragraph (k) of this AD. 

(m) Credit for Previous Actions 

This paragraph provides credit for the 

actions required by paragraph (l) of this AD, 

if those actions were performed before the 

effective date of this AD using Boeing Alert 

Service Bulletin 767–28A0104, dated January 

25, 2011. 

(n) 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–ANM– 

Seattle-ACO–AMOC–Requests@faa.gov. 

(2) Before using any approved AMOC, 

notify your appropriate principal inspector, 

or lacking a principal inspector, the manager 

of the local flight standards district office/ 

certificate holding district office. 

(3) AMOCs approved previously in 

accordance with AD 2000–11–06, 

Amendment 39–11754 (65 FR 34928, June 1, 

2000; corrected August 1, 2000 (65 FR 

46862)), are approved as AMOCs with the 

corresponding requirements of this AD. 

Compliance time extensions approved 

previously in accordance with AD 2000–11– 

06 are not approved as AMOCs for the 

compliance times required by paragraph (k) 

of this AD. 

(o) Related Information 

(1) For more information about this AD, 

contact Rebel Nichols, Aerospace Engineer, 

Propulsion Branch, ANM–140S, FAA, Seattle 

Aircraft Certification Office, 1601 Lind 

Avenue SW., Renton, Washington 98057– 

3356; phone: 425–917–6509; fax: 425–917– 

6590; email: rebel.nichols@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. 

(3) 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 June 22, 

2012. 

Jeffrey Duven, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2012–16099 Filed 6–29–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 120 

[Docket No.: FAA–2012–0688; Notice No. 

12–04] 

RIN 2120–AK01 

Combined Drug and Alcohol Testing 

Programs 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: This rulemaking would allow 

air carrier operators and commuter or 

on-demand operators that also conduct 

commercial air tour operations to 

combine the drug and alcohol testing 

required for each operation into one 

testing program. The current rule 

requires those operators to conduct 

separate testing programs for their air 


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