Federal Register / Vol. 72, No. 98 / Tuesday, May 22, 2007 / Rules and Regulations 28597 

applicable corrective actions; and, except as 

provided in paragraph (j) of this AD, install 

sleeving over the wire bundles; in accordance 

with Boeing Alert Service Bulletin 727–

28A0126, dated May 24, 1999; Boeing 

Service Bulletin 727–28A0126, Revision 1, 

dated May 18, 2000; or Boeing Alert Service 

Bulletin 727–28A0132, dated February 22, 

2007. 

Note 1: For the purposes of this AD, a 

detailed inspection is: ‘‘An intensive 

examination of a specific item, installation, 

or assembly to detect damage, failure, or 

irregularity. Available lighting is normally 

supplemented with a direct source of good 

lighting at an intensity deemed appropriate. 

Inspection aids such as mirror, magnifying 

lenses, etc., may be necessary. Surface 

cleaning and elaborate procedures may be 

required.’’

Installation: Possible Deferral 

(j) Installation of sleeving over the wire 

bundles, as required by paragraph (i) of this 

AD, may be deferred if, within 18 months or 

6,000 flight hours, whichever occurs first, 

after accomplishment of the inspection and 

applicable corrective actions required by 

paragraph (i), the following actions are 

accomplished: Perform a detailed inspection 

of the in-tank fuel boost pump wire bundles, 

and applicable corrective actions; and install 

sleeving over the wire bundles; in accordance 

with Boeing Alert Service Bulletin 727–

28A0126, dated May 24, 1999, or Boeing 

Service Bulletin 727–28A0126, Revision 1, 

dated May 18, 2000; or Boeing Alert Service 

Bulletin 727–28A0132, dated February 22, 

2007. 

Repetitive Inspections and Corrective 

Actions 

(k) Repeat the detailed inspection and 

applicable corrective actions required by 

paragraphs (i) and (j) of this AD at intervals 

not to exceed 30,000 flight hours, until the 

initial inspection, applicable corrective 

actions, and engine fuel suction feed 

operational test required by paragraph (l) of 

this AD have been done. 

New Requirements of This AD 

Inspection, Test, and Related Investigative 

and Corrective Actions 

(l) For all airplanes: Within 120 days after 

the effective date of this AD or 5,000 flight 

hours after the last inspection or corrective 

action done before the effective date of this 

AD as required by paragraph (i), (j), or (k), as 

applicable, of this AD, whichever occurs 

later, do a detailed inspection for damage of 

the sleeve and electrical wire of the fuel 

boost pump, and do an engine fuel suction 

feed operational test; and, before further 

flight, do related investigative and corrective 

actions, as applicable; by doing all applicable 

actions in and in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 727–28A0132, dated 

February 22, 2007. Repeat the detailed 

inspection and engine fuel suction feed 

operational test thereafter at intervals not to 

exceed 15,000 flight cycles. Accomplishment 

of the initial inspection, applicable corrective 

actions, and engine fuel suction feed 

operational test of this paragraph terminates 

the requirements of paragraphs (i), (j), and (k) 

of this AD. 

Inspection Report and Disposition of 

Damaged Parts 

(m) At the applicable time(s) specified in 

paragraph (m)(1) or (m)(2) of this AD: Submit 

a report of the findings (both positive and 

negative) of any inspection required by this 

AD and send any damaged parts to the 

manufacturer, as described in Boeing Alert 

Service Bulletin 727–28A0132, dated 

February 22, 2007. The report must include 

the information specified in Appendix A of 

the alert service bulletin. Under the 

provisions of the Paperwork Reduction Act 

(44 U.S.C. 3501 et seq.), the Office of 

Management and Budget (OMB) has 

approved the information collection 

requirements contained in this AD and has 

assigned OMB Control Number 2120–0056. 

(1) For any inspection done after the 

effective date of this AD: Submit the report 

within 30 days after the inspection. 

(2) For any inspection done before the 

effective date of this AD: Submit the report 

within 30 days after the effective date of this 

AD. 

Alternative Methods of Compliance 

(AMOCs) 

(n)(1) The Manager, Seattle Aircraft 

Certification Office (ACO), FAA, has the 

authority to approve AMOCs for this AD, if 

requested in accordance with the procedures 

found in 14 CFR 39.19. 

(2) To request a different method of 

compliance or a different compliance time 

for this AD, follow the procedures in 14 CFR 

39.19. Before using any approved AMOC on 

any airplane to which the AMOC applies, 

notify your appropriate principal inspector 

(PI) in the FAA Flight Standards District 

Office (FSDO), or lacking a PI, your local 

FSDO. 

(3) AMOCs approved previously in 

accordance with AD 99–12–52 are approved 

as AMOCs for the corresponding provisions 

of this AD. 

Material Incorporated by Reference 

(o) You must use applicable Boeing service 

bulletins specified in Table 1 of this AD to 

perform the actions that are required by this 

AD, unless the AD specifies otherwise. 

TABLE 1.—ALL MATERIAL INCORPORATED BY REFERENCE

Boeing service information Revision level Date 

Alert Service Bulletin 727–28A0126 .................................................................... Original .................................................. May 24, 1999. 

Alert Service Bulletin 727–28A0132 .................................................................... Original .................................................. February 22, 2007. 

Service Bulletin 727–28A0126 ............................................................................. 1 ............................................................ May 18, 2000. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

Boeing Alert Service Bulletin 727–28A0132, 

dated February 22, 2007; and Boeing Service 

Bulletin 727–28A0126, Revision 1, dated 

May 18, 2000; in accordance with 5 U.S.C. 

552(a) and 1 CFR part 51. 

(2) On June 28, 1999 (64 FR 33394, June 

23, 1999), the Director of the Federal Register 

approved the incorporation by reference of 

Boeing Alert Service Bulletin 727–28A0126, 

dated May 24, 1999. 

(3) Contact Boeing Commercial Airplanes, 

P.O. Box 3707, Seattle, Washington 98124–

2207, for a copy of this service information. 

You may review copies at the FAA, 

Transport Airplane Directorate, 1601 Lind 

Avenue, SW., Renton, Washington; or at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http:// 

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued in Renton, Washington, on May 1, 

2007. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E7–9799 Filed 5–21–07; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2007–28253; Directorate 

Identifier 2007–NM–031–AD; Amendment 

39–15064; AD 2007–11–07] 

RIN 2120–AA64 

Airworthiness Directives; Boeing 

Model 737–100, –200, –200C, –300, 

–400, and –500 Series Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 


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28598 Federal Register / Vol. 72, No. 98 / Tuesday, May 22, 2007 / Rules and Regulations 

ACTION: Final rule; request for 

comments. 

SUMMARY: The FAA is superseding an 

existing airworthiness directive (AD) 

that applies to all Model 737–100, –200, 

–300, –400, and –500 series airplanes. 

The existing AD currently requires 

repetitive detailed inspections for 

damage of the electrical wire and sleeve 

that run through a conduit in the fuel 

tank to the fuel boost pump, and related 

investigative and corrective actions; as 

applicable. This new AD removes 

certain inspection requirements. This 

new AD adds repetitive detailed 

inspections for damage of the electrical 

wire and sleeve that run to the fuel 

boost pump through a conduit in the 

fuel tank, and arcing damage of the 

conduit and signs of fuel leakage into 

the conduit; replacement of the sleeve 

with a new, smaller-diameter sleeve; 

and related investigative and corrective 

actions, as applicable. This AD also 

adds airplanes to the applicability. 

Accomplishment of the initial new 

inspection and the sleeve installation 

terminates the requirements of the 

existing AD. This new AD results from 

a report of a fuel tank explosion on a 

Model 727–200F airplane on the 

ground, and a report of chafed wires and 

a damaged power cable sleeve of a fuel 

boost pump discovered during an 

inspection on a Model 737–300 

airplane. We are issuing this AD to 

detect and correct chafing of the fuel 

boost pump electrical wiring and 

leakage of fuel into the conduit, and to 

prevent electrical arcing between the 

wiring and the surrounding conduit, 

which could result in arc-through of the 

conduit, and consequent fire or 

explosion of the fuel tank. 

DATES: This AD becomes effective June 

6, 2007. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of June 6, 2007. 

On November 12, 1999 (64 FR 54763, 

October 8, 1999), the Director of the 

Federal Register approved the 

incorporation by reference of Boeing 

Alert Service Bulletin 737–28A1120, 

Revision 2, dated November 26, 1998. 

On October 15, 1998 (63 FR 52152, 

September 30, 1998), the Director of the 

Federal Register approved the 

incorporation by reference of Boeing 

Alert Service Bulletin 737–28A1120, 

Revision 1, dated May 28, 1998. 

On June 29, 1998 (63 FR 34271, June 

24, 1998), the Director of the Federal 

Register approved the incorporation by 

reference of Boeing Alert Service 

Bulletin 737–28A1120, dated April 24, 

1998, as revised by Notice of Status 

Change NSC 01, dated May 7, 1998, 

Notice of Status Change NSC 02, dated 

May 8, 1998, and Notice of Status 

Change NSC 03, dated May 9, 1998. 

We must receive any comments on 

this AD by July 23, 2007. 

ADDRESSES: Use one of the following 

addresses to submit comments on this 

AD. 

• DOT Docket Web site: Go to 

http://dms.dot.gov and follow the 

instructions for sending your comments 

electronically. 

• Government-wide rulemaking Web 

site: Go to http://www.regulations.gov 

and follow the instructions for sending 

your comments electronically. 

• Mail: Docket Management Facility; 

U.S. Department of Transportation, 400 

Seventh Street, SW., Nassif Building, 

Room PL–401, Washington, DC 20590. 

• Fax: (202) 493–2251. 

• Hand Delivery: Room PL–401 on 

the plaza level of the Nassif Building, 

400 Seventh Street, SW., Washington, 

DC, between 9 a.m. and 5 p.m., Monday 

through Friday, except Federal holidays. 

Contact Boeing Commercial 

Airplanes, P.O. Box 3707, Seattle, 

Washington 98124–2207, for service 

information identified in this AD. 

You may examine the contents of the 

AD docket on the Internet at http:// 

dms.dot.gov, or in person at the Docket 

Management Facility, U.S. Department 

of Transportation, 400 Seventh Street, 

SW., Room PL–401, Washington, DC. 

This docket number is FAA–2007–

28253; the directorate identifier for this 

docket is 2007–NM–031–AD. 

FOR FURTHER INFORMATION CONTACT: 

Suzanne Lucier, Aerospace Engineer, 

Propulsion Branch, ANM–140S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 917–6438; fax (425) 917–6590. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On September 29, 1999, we issued AD 

99–21–15, amendment 39–11360 (64 FR 

54763, October 8, 1999). That AD 

applies to certain Boeing Model 737–

100, –200, –300, –400, and –500 series 

airplanes. That AD requires repetitive 

detailed inspections for damage of the 

electrical wire and sleeve that run 

through a conduit in the fuel tank to the 

fuel boost pump, and related 

investigative and corrective actions, as 

applicable. That AD resulted from 

reports of severe wear of the fuel boost 

pump wiring due to chafing between the 

wiring and the surrounding conduit 

inside the fuel tank, pin-hole-sized 

holes in the conduit that appear to be 

the result of arc-through of the conduit, 

and exposure of the main tank boost 

pump wire conductor inside a conduit 

and signs of arcing to the wall of the 

conduit. The actions specified in that 

AD are intended to detect and correct 

chafing and prevent electrical arcing 

between the fuel boost pump electrical 

wiring and the surrounding conduit, 

which could result in arc-through of the 

conduit, and consequent fire or 

explosion of the fuel tank. 

Actions Since AD Was Issued 

Since we issued that AD, we received 

a report that a fuel tank explosion 

occurred on a Model 727–200F airplane 

on the ground. Investigation revealed 

evidence of arcing in the metal conduit 

that carries power wires from the front 

spar through the fuel tank to the dry bay 

of the #1 aft fuel boost pump. In a 

separate incident, we received a report 

from Boeing indicating that chafed 

wires and a damaged power cable sleeve 

of a fuel boost pump were discovered 

during a repetitive inspection of the 

power cable and sleeve of a Model 737–

300 airplane; that inspection was done 

at approximately 21,000 flight hours 

rather than the repetitive interval of 

30,000 flight hours specified by the 

existing AD. The fuel boost pump 

installation on certain Model 737 

airplanes is almost identical to the 

installation on Model 727 airplanes. 

We have also determined that Model 

737–200C series airplanes are also 

subject to the unsafe condition 

identified in AD 99–21–15. 

Other Relevant Rulemaking 

Operators should note that we are 

considering issuing a separate AD to 

address the identified unsafe condition 

as it relates to Model 727 airplanes. 

Relevant Service Information 

We have reviewed Boeing Alert 

Service Bulletin 737–28A1263, Revision 

1, dated March 19, 2007. This service 

bulletin differs from the service 

information cited in AD 99–21–15 in the 

following ways. The alert service 

bulletin describes procedures for 

performing new repetitive detailed 

inspections for damage of the electrical 

wire and sleeve that run to the fuel 

boost pump through a conduit in the 

fuel tank, and arcing damage of the 

conduit and signs of fuel leakage into 

the conduit; replacing the sleeve with a 

new, smaller-diameter sleeve; 

performing related investigative and 

corrective actions, as applicable; and 

reporting inspection results and 

returning damaged parts to the 

manufacturer. The repetitive interval for 

the detailed inspections is 15,000 flight 

hours (rather than 30,000 flight hours, 


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Federal Register / Vol. 72, No. 98 / Tuesday, May 22, 2007 / Rules and Regulations 28599 

as required by AD 99–21–15). Related 

investigative and corrective actions 

include replacing, with BMS 13–

60T09C03G018 wire, any wire that is 

damaged or has any part number other 

than BMS 13–60T09C03G018 or BMS 

13–60T12C03G018; doing leak testing of 

the conduit if signs of fuel are 

discovered on the wire or sleeve during 

any inspection; and repairing any 

damaged conduit or replacing it with a 

new conduit. 

FAA’s Determination and Requirements 

of This AD 

The unsafe condition described 

previously is likely to exist or develop 

on other airplanes of the same type 

design. For this reason, we are issuing 

this AD to supersede AD 99–21–15. This 

new AD retains certain requirements of 

the existing AD. This AD also requires 

accomplishing the actions specified in 

the alert service bulletin described 

previously. 

Changes to Existing AD 

Instead of restating all of the 

corrective actions specified in AD 99–

21–15, that is, paragraphs (h), (i), (j), and 

(k), we simplified these requirements by 

consolidating them into paragraph (j) in 

this AD. We have verified that all of the 

information of paragraphs (h), (i), (j), 

and (k) of AD 99–21–15 is contained in 

the service bulletin references identified 

in paragraph (j) of this AD. 

Clarification of Applicability 

The applicability of AD 99–21–15 did 

not specifically list Model 737–200C 

series airplanes. Likewise, the service 

information (Boeing Service Bulletin 

737–28A1120, original version, Revision 

1, and Revision 2) cited in that AD did 

not specifically identify Model 737–

200C series airplanes in the effectivity, 

although Revision 3 did identify them. 

Because the unsafe condition could 

occur on those airplanes, this AD adds 

them to the applicability to ensure that 

the actions required by this AD are 

accomplished on all affected airplanes. 

We recognize that some of these 

airplanes might have already been 

inspected as specified in the existing 

AD. In order to give credit for work 

accomplished on these airplanes, this 

AD adds a compliance time for the 

initial inspection relative to the date of 

the most recent inspection done in 

accordance with Service Bulletin 737–

28A1120. 

Interim Action 

We consider this AD interim action. If 

final action is later identified, we may 

consider further rulemaking then. 

Explanation of Compliance Time 

The compliance time for the new 

inspection in this AD is 120 days. Based 

on the large number of affected U.S.- 

registered airplanes and the amount of 

time required to accomplish the 

required actions, including corrective 

actions, we consider that this 

compliance time is necessary to avoid 

unnecessarily disrupting flight 

schedules. 

FAA’s Determination of the Effective 

Date 

An unsafe condition exists that 

requires the immediate adoption of this 

AD; therefore, providing notice and 

opportunity for public comment before 

the AD is issued is impracticable, and 

good cause exists to make this AD 

effective in less than 30 days. 

Comments Invited 

This AD is a final rule that involves 

requirements that affect flight safety and 

was not preceded by notice and an 

opportunity for public comment; 

however, we invite you to submit any 

relevant written data, views, or 

arguments regarding this AD. Send your 

comments to an address listed in the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2007–28253; Directorate Identifier 

2007–NM–031–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of the AD that might suggest a 

need to modify it. 

We will post all comments we 

receive, without change, to http:// 

dms.dot.gov, including any personal 

information you provide. We will also 

post a report summarizing each 

substantive verbal contact with FAA 

personnel concerning this AD. Using the 

search function of that Web site, anyone 

can find and read the comments in any 

of our dockets, including the name of 

the individual who sent the comment 

(or signed the comment on behalf of an 

association, business, labor union, etc.). 

You may review the DOT’s complete 

Privacy Act Statement in the Federal 

Register published on April 11, 2000 

(65 FR 19477–78), or you may visit 

http://dms.dot.gov. 

Examining the Docket 

You may examine the AD docket on 

the Internet at http://dms.dot.gov, or in 

person at the Docket Management 

Facility office between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. The Docket 

Management Facility office (telephone 

(800) 647–5227) is located on the plaza 

level of the Nassif Building at the DOT 

street address stated in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after the Docket 

Management System receives them. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

Section 106, describes the authority of 

the FAA Administrator. Subtitle VII, 

Aviation Programs, describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in Subtitle VII, 

Part A, Subpart III, Section 44701, 

‘‘General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We have determined that this AD will 

not have federalism implications under 

Executive Order 13132. This AD will 

not have a substantial direct effect on 

the States, on the relationship between 

the national government and the States, 

or on the distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify that the regulation: 

1. Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

2. Is not a ‘‘significant rule’’ under the 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979); and 

3. Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

We prepared a regulatory evaluation 

of the estimated costs to comply with 

this AD and placed it in the AD docket. 

See the ADDRESSES section for a location 

to examine the regulatory evaluation. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

■ Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends part 39 of the Federal 

Aviation Regulations (14 CFR part 39) as 

follows: 


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28600 Federal Register / Vol. 72, No. 98 / Tuesday, May 22, 2007 / Rules and Regulations 

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 Federal Aviation 

Administration (FAA) amends § 39.13 

by removing amendment 39–11360 (64 

FR 54763, October 8, 1999) and adding 

the following new airworthiness 

directive (AD): 

2007–11–07 Boeing: Docket No. FAA–2007–

28253; Directorate Identifier 2007–NM–

031–AD; Amendment 39–15064. 

Effective Date 

(a) This AD becomes effective June 6, 2007. 

Affected ADs 

(b) This AD supersedes AD 99–21–15. 

Applicability 

(c) This AD applies to all Boeing Model 

737–100, –200, –200C, –300, –400, and –500 

series airplanes, certificated in any category. 

Unsafe Condition 

(d) This AD results from a report of a fuel 

tank explosion on a Model 727–200F 

airplane on the ground, and a report of 

chafed wires and a damaged power cable 

sleeve of a fuel boost pump discovered 

during an inspection on a Model 737–300 

airplane. (The fuel boost pump installation 

on certain Model 737 airplanes is almost 

identical to the installation on Model 727 

airplanes.) We are issuing this AD to detect 

and correct chafing of the fuel boost pump 

electrical wiring and leakage of fuel into the 

conduit, and to prevent electrical arcing 

between the wiring and the surrounding 

conduit, which could result in arc-through of 

the conduit, and consequent fire or explosion 

of the fuel tank. 

Compliance 

(e) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified, unless the 

actions have already been done. 

Restatement of Certain Requirements of AD 

99–21–15 

Certain Inspections Required by AD 98–11–

52 

(f) For Model 737–100, –200, –300, –400, 

and –500 series airplanes: Prior to the 

accumulation of 30,000 total flight hours or 

within 45 days after June 29, 1998 (the 

effective date of AD 98–11–52, amendment 

39–10611, which was superseded by AD 98–

19–09), whichever occurs later, remove the 

fuel boost pump wiring from the in-tank 

conduit for the aft boost pumps in main tanks 

numbers 1 and 2, and the center tank left and 

right boost pumps, and perform a detailed 

visual inspection to detect damage of the 

wiring, in accordance with the procedures 

specified in Boeing Alert Service Bulletin 

737–28A1120, dated April 24, 1998, as 

revised by Notices of Status Change NSC 01, 

dated May 7, 1998, NSC 02, dated May 8, 

1998, and NSC 03, dated May 9, 1998; 

Revision 1, dated May 28, 1998; or Revision 

2, dated November 26, 1998. 

Inspections Required by AD 98–19–09 

(g) For Model 737–100, –200, –300, –400, 

and –500 series airplanes that have 

accumulated 20,000 or more total flight hours 

and less than 30,000 total flight hours as of 

October 15, 1998 (the effective date of AD 

98–19–09, amendment 39–10751, which was 

superseded by AD 99–21–15): Within 60 days 

after October 15, 1998, remove the fuel boost 

pump wiring from the in-tank conduit for the 

aft boost pumps in main tanks numbers 1 and 

2, and the center tank left and right boost 

pumps, and perform a detailed visual 

inspection to detect damage of the wiring; in 

accordance with the procedures specified in 

Boeing Alert Service Bulletin 737–28A1120, 

dated April 24, 1998, as revised by Notices 

of Status Change NSC 01, dated May 7, 1998, 

NSC 02, dated May 8, 1998, and NSC 03, 

dated May 9, 1998; Revision 1, dated May 28, 

1998; or Revision 2, dated November 26, 

1998. 

Inspections Required by AD 99–21–15 

(h) For Model 737–100, –200, –300, –400, 

and –500 series airplanes: Remove the fuel 

boost pump wiring from the in-tank conduit 

for the aft boost pumps in main tanks 

numbers 1 and 2, and the center tank left and 

right boost pumps, and perform a detailed 

visual inspection to detect damage of the 

wiring; at the time specified in paragraph 

(h)(1) or (h)(2) of this AD, as applicable. 

Perform these actions in accordance with the 

procedures specified in Boeing Alert Service 

Bulletin 737–28A1120, dated April 24, 1998, 

as revised by Notices of Status Change NSC 

01, dated May 7, 1998, NSC 02, dated May 

8, 1998, and NSC 03, dated May 9, 1998; 

Revision 1, dated May 28, 1998; or Revision 

2, dated November 26, 1998. 

(1) For airplanes having line numbers 1 

through 3072 inclusive that have 

accumulated less than 20,000 total flight 

hours as of October 15, 1998: Inspect at the 

earlier of the times specified in paragraphs 

(h)(1)(i) and (h)(1)(ii) of this AD. 

(i) Prior to the accumulation of 20,000 total 

flight hours, or within 60 days after 

November 12, 1999 (the effective date of AD 

99–21–15), whichever occurs later. 

(ii) Within 24 months after November 12, 

1999. 

(2) For airplanes having line numbers 3073 

and subsequent: Inspect prior to the 

accumulation of 30,000 total flight hours. 

Repetitive Intervals 

(i) For Model 737–100, –200, –300, –400, 

and –500 series airplanes: Repeat the 

inspection required by paragraph (f), (g), or 

(h) of this AD, as applicable, at intervals not 

to exceed 30,000 flight hours after initial 

accomplishment of the applicable inspection, 

until the initial inspection, applicable 

corrective actions, and sleeve installation 

required by paragraph (k) of this AD have 

been done. 

Corrective Actions 

(j) If any discrepancy is found during any 

inspection required by paragraph (f), (g), (h), 

or (i) of this AD: Before further flight, repair 

the discrepancy in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 737–28A1120, dated April 

24, 1998, as revised by Notices of Status 

Change NSC 01, dated May 7, 1998, NSC 02, 

dated May 8, 1998, and NSC 03, dated May 

9, 1998; Revision 1, dated May 28, 1998; 

Revision 2, dated November 26, 1998; or 

Revision 3, dated April 26, 2001. 

New Requirements of This AD 

Inspection and Related Investigative and 

Corrective Actions 

(k) At the applicable time specified by 

paragraph (k)(1) or (k)(2) of this AD: Do a 

detailed inspection for damage of the sleeve 

and electrical wire of the fuel boost pump; 

and, before further flight, install a new, 

smaller-diameter sleeve, and do related 

investigative and corrective actions, as 

applicable; in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 737–28A1263, Revision 1, 

dated March 19, 2007. Thereafter, repeat the 

detailed inspection at intervals not to exceed 

15,000 flight cycles. Accomplishment of the 

initial inspection, applicable corrective 

actions, and sleeve installation required by 

this paragraph terminates the requirements of 

paragraphs (f), (g), (h), and (i) of this AD. 

(1) For Model 737–100, –200, –300, –400, 

and –500 series airplanes: Within 120 days 

after the effective date of this AD, or within 

5,000 flight hours after the last inspection or 

repair done as required by paragraph (f), (g), 

(h), or (i), as applicable, of this AD, 

whichever occurs later. 

(2) For Model 737–200C series airplanes: 

Within 120 days after the effective date of 

this AD, or within 5,000 flight hours after the 

last inspection or repair done in accordance 

with any version of Boeing Alert Service 

Bulletin 737–28–1120, whichever occurs 

later. 

Inspection Report and Disposition of 

Damaged Parts 

(l) At the applicable time specified in 

paragraph (l)(1) or (l)(2) of this AD: Submit 

a report of the findings (both positive and 

negative) of any inspection required by 

paragraph (k) of this AD and send any 

damaged parts to the manufacturer, as 

described in Boeing Alert Service Bulletin 

737–28A1263, Revision 1, dated March 19, 

2007. The report must include the inspection 

results, a description of any discrepancies 

found, the airplane serial number, and the 

number of landings and flight hours on the 

airplane. Under the provisions of the 

Paperwork Reduction Act (44 U.S.C. 3501 et 

seq.), the Office of Management and Budget 

(OMB) has approved the information 

collection requirements contained in this AD 

and has assigned OMB Control Number 

2120–0056. 

(1) For any inspection done after the 

effective date of this AD: Submit the report 

within 30 days after the inspection. 

(2) For any inspection done before the 

effective date of this AD: Submit the report 

within 30 days after the effective date of this 

AD. 


cprice-sewell on PRODPC61 with RULES
Federal Register / Vol. 72, No. 98 / Tuesday, May 22, 2007 / Rules and Regulations 28601 

Credit for Actions Done Using Previous 

Service Information 

(m) Actions accomplished before the 

effective date of this AD in accordance with 

Boeing Service Bulletin 737–28A1263, dated 

February 19, 2007, are considered acceptable 

for compliance with the corresponding 

actions specified in this AD. 

Alternative Methods of Compliance 

(AMOCs) 

(n)(1) The Manager, Seattle Aircraft 

Certification Office (ACO), FAA, has the 

authority to approve AMOCs for this AD, if 

requested in accordance with the procedures 

found in 14 CFR 39.19. 

(2) To request a different method of 

compliance or a different compliance time 

for this AD, follow the procedures in 14 CFR 

39.19. Before using any approved AMOC on 

any airplane to which the AMOC applies, 

notify your appropriate principal inspector 

(PI) in the FAA Flight Standards District 

Office (FSDO), or lacking a PI, your local 

FSDO. 

(3) AMOCs approved previously in 

accordance with AD 99–21–15, amendment 

39–11360, are approved as AMOCs for the 

corresponding provisions of this AD. 

Material Incorporated by Reference 

(o) You must use applicable Boeing service 

bulletins specified in Table 1 of this AD to 

perform the actions that are required by this 

AD, unless the AD specifies otherwise. 

TABLE 1.—ALL MATERIAL INCORPORATED BY REFERENCE

Service Bulletin Revision level Date 

Boeing Alert Service Bulletin 737–28A1120, as revised by Notice of Status Change NSC 01, dated 

May 7, 1998, Notice of Status Change NSC 02, dated May 8, 1998, and Notice of Status Change 

NSC 03, dated May 9, 1998.

Original ........... April 24, 1998. 

Boeing Alert Service Bulletin 737–28A1120 ............................................................................................ 1 ...................... May 28, 1998. 

Boeing Alert Service Bulletin 737–28A1120 ............................................................................................ 2 ...................... November 26, 1998. 

Boeing Service Bulletin 737–28A1120 ..................................................................................................... 3 ...................... April 26, 2001. 

Boeing Alert Service Bulletin 737–28A1263 ............................................................................................ 1 ...................... March 19, 2007. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

Boeing Alert Service Bulletin 737–28A1263, 

Revision 1, dated March 19, 2007; and 

Boeing Service Bulletin 737–28A1120, 

Revision 3, dated April 26, 2001; in 

accordance with 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) On November 12, 1999 (64 FR 54763, 

October 8, 1999), the Director of the Federal 

Register approved the incorporation by 

reference of Boeing Alert Service Bulletin 

737–28A1120, Revision 2, dated November 

26, 1998. 

(3) On October 15, 1998 (63 FR 52152, 

September 30, 1998), the Director of the 

Federal Register approved the incorporation 

by reference of Boeing Alert Service Bulletin 

737–28A1120, Revision 1, dated May 28, 

1998. 

(4) On June 29, 1998 (63 FR 34271, June 

24, 1998), the Director of the Federal Register 

approved the incorporation by reference of 

Boeing Alert Service Bulletin 737–28A1120, 

dated April 24, 1998, as revised by Notice of 

Status Change NSC 01, dated May 7, 1998, 

Notice of Status Change NSC 02, dated May 

8, 1998, and Notice of Status Change NSC 03, 

dated May 9, 1998. 

(5) Contact Boeing Commercial Airplanes, 

P.O. Box 3707, Seattle, Washington 98124–

2207, for a copy of this service information. 

You may review copies at the FAA, 

Transport Airplane Directorate, 1601 Lind 

Avenue, SW., Renton, Washington; or at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http:// 

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued in Renton, Washington, on May 2, 

2007. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E7–9801 Filed 5–21–07; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF JUSTICE 

Drug Enforcement Administration 

21 CFR Part 1313 

[Docket No. DEA–292N] 

RIN 1117–AB06 

Implementation of the Combat 

Methamphetamine Epidemic Act of 

2005; Notice of Transfers Following 

Importation or Exportation; Temporary 

Stay of Certain Provisions 

AGENCY: Drug Enforcement 

Administration (DEA), Justice. 

ACTION: Interim final rule with request 

for comment; temporary stay of 

provisions. 

SUMMARY: On April 9, 2007, the Drug 

Enforcement Administration (DEA) 

published an Interim Final Rule with 

Request for Comment in the Federal 

Register (72 FR 17401) implementing 

the provisions of section 716 of the 

Combat Methamphetamine Epidemic 

Act of 2005 (CMEA) (21 U.S.C. 971 as 

amended), enacted March 9, 2006, 

which required additional reporting for 

import, export, and international 

transactions involving all List I and List 

II chemicals. Subsequent to publication 

of the Interim Final Rule, DEA received 

both written and verbal comments from 

the regulated industry requesting the 

delay of the effective date of the 

rulemaking to allow industry more time 

to fully comply with the new 

provisions. The rule became effective 

May 9, 2007. After careful consideration 

of the comments received, DEA is 

temporarily staying the provisions of the 

Interim Final Rule with Request for 

Comment published April 9, 2007, by 

30 days, from May 9, 2007 to June 8, 

2007. 

DATES: Effective May 22, 2007, through 

June 7, 2007, the provisions of 21 CFR 

1313.12(c)(1)(ii), 1313.13(c)(5), 1313.16, 

1313.17, 1313.26, 1313.27, 1313.32(d), 

1313.32(e), and 1313.35 are temporarily 

stayed. 

FOR FURTHER INFORMATION CONTACT: 

Mark W. Caverly, Chief, Liaison and 

Policy Section, Office of Diversion 

Control, Drug Enforcement 

Administration, Washington, DC 20537 

at (202) 307–7297. 

SUPPLEMENTARY INFORMATION: 

Background 

On March 9, 2006, the President 

signed the Combat Methamphetamine 

Epidemic Act of 2005 (CMEA), which is 

Title VII of the USA PATRIOT 

Improvement and Reauthorization Act 

of 2005 (Pub. L. 109–177). On April 9, 

2007, the Drug Enforcement 

Administration (DEA) published an 

Interim Final Rule with Request for 

Comment (72 FR 17401) implementing 

section 716 of the CMEA. That section 

addressed the importation, exportation, 

and international transactions of all List 

I and List II chemicals. Briefly, section 

716 of the CMEA (21 U.S.C. 971 as 


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