Federal Register / Vol. 68, No. 166 / Wednesday, August 27, 2003 / Rules and Regulations 51439

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. 2002–NM–128–AD; Amendment 

39–13269; AD 2003–16–16] 

RIN 2120–AA64 

Airworthiness Directives; Boeing 

Model 747–400 Series Airplanes 

Equipped With General Electric Model 

CF6–80C2 Series Engines

AGENCY: Federal Aviation 

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment supersedes 

an existing airworthiness directive (AD), 

applicable to certain Boeing Model 747–

400 series airplanes, that currently 

requires repetitive tests of the cone 

brake of the central drive unit (CDU) of 

the thrust reversers, and corrective 

actions if necessary. This amendment 

requires installation of a thrust reverser 

actuation system (TRAS) lock and 

various related modifications and 

installations. Following installation of 

the TRAS lock, this action also requires 

repetitive functional tests of the TRAS 

lock, and corrective action if necessary. 

These actions are intended to prevent an 

inadvertent deployment of a thrust 

reverser during flight, which could 

result in loss of control of the airplane.

DATES: Effective October 1, 2003. 

The incorporation by reference of 

certain publications, as listed in the 

regulations, is approved by the Director 

of the Federal Register as of October 1, 

2003. 

The incorporation by reference of 

certain other publications, as listed in 

the regulations, was approved 

previously by the Director of the Federal 

Register as of September 6, 2000 (65 FR 

47252, August 2, 2000). 

The incorporation by reference of 

certain other publications, as listed in 

the regulations, was approved 

previously by the Director of the Federal 

Register as of March 13, 2000 (65 FR 

5742, February 7, 2000). 

The incorporation by reference of 

certain other publications, as listed in 

the regulations, was approved 

previously by the Director of the Federal 

Register as of August 25, 1999 (64 FR 

39003, July 21, 1999).

ADDRESSES: The service information 

referenced in this AD may be obtained 

from Boeing Commercial Airplane 

Group, P.O. Box 3707, Seattle, 

Washington 98124–2207; and 

Distribution, Lockheed Martin 

Technical Services, 1330 Kemper 

Meadow Drive, suite 110–C, Cincinnati, 

Ohio 45240. This information may be 

examined at the Federal Aviation 

Administration (FAA), Transport 

Airplane Directorate, Rules Docket, 

1601 Lind Avenue, SW., Renton, 

Washington; or at the Office of the 

Federal Register, 800 North Capitol 

Street, NW., suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT:

Sulmo Mariano, Aerospace Engineer, 

Propulsion Branch, ANM–140S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue, SW., Renton, 

Washington 98055–4056; telephone 

(425) 917–6501; fax (425) 917–6590.

SUPPLEMENTARY INFORMATION: A 

proposal to amend part 39 of the Federal 

Aviation Regulations (14 CFR part 39) 

by superseding AD 2000–09–03, 

amendment 39–11711 (65 FR 25829, 

May 4, 2000), which is applicable to 

certain Boeing Model 747–400 series 

airplanes, was published in the Federal 

Register on January 30, 2003 (68 FR 

4731). The action proposed to continue 

to require repetitive tests of the cone 

brake of the central drive unit of the 

thrust reversers, and corrective actions 

if necessary. The action proposed to add 

new requirements for installation of a 

thrust reverser actuation system (TRAS) 

lock and various related modifications 

and installations. The action also 

proposed to require, following 

installation of the TRAS lock, repetitive 

functional tests of the TRAS lock, and 

corrective action if necessary.

Comments 

Interested persons have been afforded 

an opportunity to participate in the 

making of this amendment. Due 

consideration has been given to the 

comments received from a single 

commenter. 

Request To Add Additional Sources of 

Service Information 

The commenter notes that there are 

later revisions available for certain 

service bulletins referenced in the 

proposed AD. The commenter points 

out the following: 

• Lockheed Martin is now Middle 

River Aircraft Systems (MRAS). 

• Lockheed Martin Service Bulletin 

78–1007, Revision 1, dated March 18, 

1997, has been superseded by MRAS 

Service Bulletin 78–1007, Revision 2, 

dated March 10, 1998. 

• Lockheed Martin Service Bulletin 

78–1020, Revision 2, dated March 20, 

1997, has been superseded by MRAS 

Service Bulletin 78–1020, Revision 3, 

dated March 16, 1998; and MRAS CF6–

80C2B Service Bulletin 78–1020, 

Revision 4, dated October 10, 2002.

The commenter notes that no additional 

work is necessary per the new revisions 

of the service bulletins. 

We infer that the commenter is 

requesting that we revise the final rule 

to include references to the later 

revisions of the service bulletins. We 

concur and have revised paragraphs 

(d)(2)(i) and (d)(2)(iii) of this AD to 

reference the service bulletin revisions 

cited by the commenter as additional 

acceptable sources of service 

information. 

Request To Accept Additional Software 

Versions 

The same commenter notes that 

Boeing Service Bulletin 747–31–2242, 

dated April 18, 1996, which is cited in 

paragraph (d)(2)(iv) of the proposed AD, 

specifies installation of integrated 

display system (IDS) software version 

995–0017–012. The commenter 

similarly notes that Boeing Service 

Bulletin 747–45–2016 (Revision 1, dated 

May 2, 1996), which is cited in 

paragraph (d)(2)(v) of the proposed AD, 

specifies installation of central 

maintenance computer (CMC) software 

version 685–2270–009. The commenter 

points out that, since the issuance of 

those service bulletins, the 

manufacturer has released several 

additional software versions. The 

commenter requests that we include the 

additional software versions as 

acceptable parts for the purposes of the 

proposed AD. 

We concur and have added references 

to acceptable versions of the IDS and 

CMC software into paragraphs (d)(2)(iv) 

and (d)(2)(v) of this AD, respectively. 

We note, however, that the 

manufacturer has delayed release of one 

of the CMC software versions to which 

the commenter refers, 685–2270–012. 

Because we are unable to determine 

whether that version would be 

acceptable for compliance with this AD, 

this final rule does not refer to that 

version. 

Conclusion 

After careful review of the available 

data, including the comments noted 

above, the FAA has determined that air 

safety and the public interest require the 

adoption of the rule with the changes 

previously described. The FAA has 

determined that these changes will 

neither increase the economic burden 

on any operator nor increase the scope 

of the AD. 

Changes to 14 CFR Part 39/Effect on the 

AD 

On July 10, 2002, the FAA issued a 

new version of 14 CFR part 39 (67 FR 

47997, July 22, 2002), which governs the 

51440 Federal Register / Vol. 68, No. 166 / Wednesday, August 27, 2003 / Rules and Regulations 

FAA’s airworthiness directives system. 

The regulation now includes material 

that relates to altered products, special 

flight permits, and alternative methods 

of compliance. Because we have now 

included this material in part 39, we no 

longer need to include it in each 

individual AD. However, for clarity and 

consistency in this final rule, we have 

retained the language of the NPRM 

regarding that material. 

Change to Labor Rate Estimate 

Since we issued the proposed AD, we 

have reviewed the figures we have used 

over the past several years to calculate 

AD costs to operators. To account for 

various inflationary costs in the airline 

industry, we find it necessary to 

increase the labor rate used in these 

calculations from $60 per work hour to 

$65 per work hour. The cost impact 

information, below, reflects this 

increase in the specified hourly labor 

rate. 

Cost Impact 

There are approximately 145 

airplanes of the affected design in the 

worldwide fleet. The FAA estimates that 

8 airplanes of U.S. registry will be 

affected by this AD. 

The functional test that is currently 

required by AD 2000–09–03 takes 

approximately 12 work hours per 

airplane to accomplish, at an average 

labor rate of $65 per work hour. Based 

on these figures, the cost impact of the 

currently required actions on U.S. 

operators is estimated to be $6,240, or 

$780 per airplane, per test cycle. 

The installations in Boeing Service 

Bulletin 747–78–2151, Revision 2, will 

take approximately 410 work hours per 

airplane to accomplish, at an average 

labor rate of $65 per work hour. 

Required parts will be provided at no 

charge. Based on these figures, the cost 

impact of this requirement on U.S. 

operators is estimated to be $213,200, or 

$26,650 per airplane. 

The installation specified in Lockheed 

Martin Service Bulletin 78–1007, 

Revision 1, or MRAS Service Bulletin 

78–1007, Revision 2, will take 

approximately 60 work hours per 

airplane to accomplish, at an average 

labor rate of $65 per work hour. 

Required parts will be provided at no 

charge. Based on these figures, the cost 

impact of this requirement on U.S. 

operators is estimated to be $31,200, or 

$3,900 per airplane. 

The installation specified in Boeing 

Service Bulletin 747–78–2132, Revision 

2, will take approximately 223 work 

hours per airplane to accomplish, at an 

average labor rate of $65 per work hour. 

Required parts will cost between 

$32,219 and $36,562 per airplane. Based 

on these figures, the cost impact of this 

requirement is estimated to be between 

$46,714 and $51,057 per airplane. The 

manufacturer may cover the cost of 

replacement parts associated with this 

service bulletin, subject to warranty 

conditions. As a result, the costs 

attributable to this required action may 

be less than stated above. 

The installation specified in Lockheed 

Martin Service Bulletin 78–1020, 

Revision 2, or MRAS Service Bulletin 

78–1020, Revision 3 or 4, will take 

approximately 16 work hours per 

airplane to accomplish, at an average 

labor rate of $65 per work hour. 

Required parts will be provided at no 

charge. Based on these figures, the cost 

impact of this requirement on U.S. 

operators is estimated to be $8,320, or 

$1,040 per airplane. 

The installation specified in Boeing 

Service Bulletin 747–31–2242 will take 

approximately 2 work hours per 

airplane to accomplish, at an average 

labor rate of $65 per work hour. The 

cost of required parts will be negligible. 

Based on these figures, the cost impact 

of this requirement is estimated to be 

$1,040, or $130 per airplane. The 

manufacturer may cover the cost of 

replacement parts and labor costs 

associated with accomplishment of this 

service bulletin, subject to warranty 

conditions. As a result, the costs 

attributable to this required action may 

be less than stated. 

The installation specified in Boeing 

Service Bulletin 747–45–2016, Revision 

1, will take approximately 3 work hours 

per airplane to accomplish, at an 

average labor rate of $65 per work hour. 

The cost of required parts will be 

negligible. Based on these figures, the 

cost impact of this requirement is 

estimated to be $1,560, or $195 per 

airplane. The manufacturer may cover 

the labor costs associated with 

accomplishment of this service bulletin, 

subject to warranty conditions. As a 

result, the costs attributable to this 

required action may be less than stated 

above.

The functional test that will be 

required following installation of the 

TRAS lock would take approximately 12 

work hours per airplane to accomplish, 

at an average labor rate of $65 per work 

hour. Based on these figures, the cost 

impact of this requirement is estimated 

to be $6,240, or $780 per airplane, per 

test cycle. 

The cost impact figures discussed 

above are based on assumptions that no 

operator has yet accomplished any of 

the requirements of this AD action, and 

that no operator would accomplish 

those actions in the future if this AD 

were not adopted. The cost impact 

figures discussed in AD rulemaking 

actions represent only the time 

necessary to perform the specific actions 

actually required by the AD. These 

figures typically do not include 

incidental costs, such as the time 

required to gain access and close up, 

planning time, or time necessitated by 

other administrative actions. 

Regulatory Impact 

The regulations adopted herein 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. Therefore, it is 

determined that this final rule does not 

have federalism implications under 

Executive Order 13132. 

For the reasons discussed above, I 

certify that this action (1) Is not a 

‘‘significant regulatory action’’ under 

Executive Order 12866; (2) is not a 

‘‘significant rule’’ under 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. A final evaluation has 

been prepared for this action and it is 

contained in the Rules Docket. A copy 

of it may be obtained from the Rules 

Docket at the location provided under 

the caption ADDRESSES.

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety.

Adoption of the Amendment

■ Accordingly, pursuant to the authority 

delegated to me by the Administrator, 

the Federal Aviation Administration 

amends part 39 of the Federal Aviation 

Regulations (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. Section 39.13 is amended by 

removing amendment 39–11711 (65 FR 

25829, May 4, 2000), and by adding a 

new airworthiness directive (AD), 

amendment 39–13269, to read as 

follows:

2003–16–16 Boeing: Amendment 39–13269. 

Docket 2002–NM–128–AD. Supersedes AD 

2000–09–03, Amendment 39–11711.

Federal Register / Vol. 68, No. 166 / Wednesday, August 27, 2003 / Rules and Regulations 51441

Applicability: Model 747–400 series 

airplanes equipped with General Electric 

(GE) Model CF6–80C2 series engines, 

certificated in any category.

Note 1: This AD applies to each airplane 

identified in the preceding applicability 

provision, regardless of whether it has been 

modified, altered, or repaired in the area 

subject to the requirements of this AD. For 

airplanes that have been modified, altered, or 

repaired so that the performance of the 

requirements of this AD is affected, the 

owner/operator must request approval for an 

alternative method of compliance in 

accordance with paragraph (h)(1) of this AD. 

The request should include an assessment of 

the effect of the modification, alteration, or 

repair on the unsafe condition addressed by 

this AD; and, if the unsafe condition has not 

been eliminated, the request should include 

specific proposed actions to address it.

Compliance: Required as indicated, unless 

accomplished previously. 

To prevent an inadvertent deployment of a 

thrust reverser during flight, which could 

result in loss of control of the airplane, 

accomplish the following: 

Requirements of AD 2000–09–03 

Repetitive Functional Tests 

(a) Within 1,000 hours time-in-service after 

the most recent test of the center drive unit 

(CDU) cone brake as specified in paragraph 

(b)(1) of AD 94–15–05, amendment 39–8976; 

or within 650 hours time-in-service after May 

19, 2000 (the effective date of AD 2000–09–

03, amendment 39–11711); whichever occurs 

later: Perform a functional test to detect 

discrepancies of the CDU cone brake on each 

thrust reverser as specified in paragraph 

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

(1) For Model 747–400 series airplanes 

equipped with thrust reversers that have not 

been modified in accordance with Boeing 

Service Bulletin 747–78–2151 or a 

production equivalent: Perform the test in 

accordance with Boeing Service Bulletin 

747–78A2166, Revision 1, dated October 9, 

1997; or paragraph 3.C. of Boeing Alert 

Service Bulletin 747–78A2166, Revision 2, 

dated March 15, 2001; or the applicable 

section of paragraph III.A. of the 

Accomplishment Instructions of Boeing 

Service Bulletin 747–78A2113, Revision 2, 

dated June 8, 1995; or Revision 3, dated 

September 11, 1997. Repeat the test thereafter 

at intervals not to exceed 650 hours time-inservice. 

(2) For Model 747–400 series airplanes 

equipped with thrust reversers that have 

been modified in accordance with Boeing 

Service Bulletin 747–78–2151 or a 

production equivalent: Perform the test in 

accordance with Appendix 1 (including 

Figure 1) of this AD, or paragraph 3.C. of 

Boeing Alert Service Bulletin 747–78A2166, 

Revision 2, dated March 15, 2001. After the 

effective date of this AD, only Boeing Alert 

Service Bulletin 747–78A2166, Revision 2, 

may be used. Repeat the test thereafter at 

intervals not to exceed 1,000 hours time-inservice.

Note 2: Accomplishment of the CDU cone 

brake test during production in accordance 

with Production Revision Record (PRR) 

80452–102 prior to May 19, 2000, is 

considered acceptable for compliance with 

the initial test required by paragraph (a) of 

this AD.

Note 3: Model 747–400 series airplanes, 

line numbers 1061 and subsequent, equipped 

with GE CF6–80C2 engines, had a third 

locking system installed during production 

in accordance with PRR 80452–102, and 

were not modified in accordance with Boeing 

Service Bulletin 747–78–2151 (which is a 

retrofit action for airplanes having line 

numbers 700 through 1060 inclusive).

Terminating Action 

(b) Accomplishment of the functional test 

of the CDU cone brake, as specified in 

paragraph (a) of this AD, constitutes 

terminating action for the repetitive tests of 

the CDU cone brake required by paragraph 

(b)(1) of AD 94–15–05. 

Corrective Action 

(c) If any functional test required by 

paragraph (a) of this AD cannot be 

successfully performed as specified in the 

referenced service bulletin, or if any 

discrepancy is detected during any 

functional test required by paragraph (a) of 

this AD, accomplish either paragraph (c)(1) 

or (c)(2) of this AD. 

(1) Prior to further flight, repair in 

accordance with Boeing Service Bulletin 

747–78A2166, Revision 1, dated October 9, 

1997; Boeing Alert Service Bulletin 747–

78A2166, Revision 2, dated March 15, 2001; 

Boeing Service Bulletin 747–78A2113, 

Revision 2, dated June 8, 1995; or Revision 

3, dated September 11, 1997. After the 

effective date of this AD, only Boeing Alert 

Service Bulletin 747–78A2166, Revision 2; or 

Boeing Service Bulletin 747–78A2113, 

Revision 2 or Revision 3; may be used.

(2) The airplane may be operated in 

accordance with the provisions and 

limitations specified in the operator’s FAAapproved Minimum Equipment List, 

provided that no more than one thrust 

reverser on the airplane is inoperative. 

New Requirements of This AD 

Installation of Thrust Reverser Actuator 

System Lock and Associated Actions 

(d) For airplanes listed in Boeing Service 

Bulletin 747–78–2151, Revision 2, dated 

January 13, 2000: Within 36 months after the 

effective date of this AD, do paragraphs (d)(1) 

and (d)(2) of this AD. 

(1) Install and activate a thrust reverser 

actuator system (TRAS) lock on each thrust 

reverser per the Accomplishment 

Instructions of Boeing Service Bulletin 747–

78–2151, Revision 1, dated August 21, 1997; 

as revised by Notice of Status Change (NSC) 

747–78–2151 NSC 04, dated November 26, 

1997; and NSC 747–78–2151 NSC 05, dated 

December 18, 1997; or Boeing Service 

Bulletin 747–78–2151, Revision 2, dated 

January 13, 2000. The procedures for 

completing the installation and activating the 

TRAS lock include replacing a certain 

microswitch pack with a new one; adding 

new wires; routing certain new wire bundles; 

changing certain wiring, circuit breakers, and 

components; installing thrust-reverser relay 

panels; and performing a functional test to 

ensure that the thrust reverser actuation 

system operates properly. 

(2) Prior to or concurrently with the 

installation required by paragraph (d)(1) of 

this AD, do the requirements of paragraphs 

(d)(2)(i), (d)(2)(ii), (d)(2)(iii), (d)(2)(iv), and 

(d)(2)(v) of this AD. 

(i) Install a bracket and fastening hardware 

for the third locking system on each thrust 

reverser, per Lockheed Martin Service 

Bulletin 78–1007, Revision 1, dated March 

18, 1997; or Middle River Aircraft Systems 

Service Bulletin 78–1007, Revision 2, dated 

March 10, 1998. 

(ii) Install wiring provisions in various 

areas of the airplane, per the 

Accomplishment Instructions of Boeing 

Service Bulletin 747–78–2132, Revision 2, 

dated December 11, 1997. 

(iii) Install a TRAS lock (also called an 

electromechanical lock or brake) and a 

flexible drive cable on each thrust reverser, 

per Lockheed Martin Service Bulletin 78–

1020, Revision 2, dated March 20, 1997; or 

Middle River Aircraft Systems Service 

Bulletin 78–1020, Revision 3, dated March 

16, 1998; or Middle River Aircraft Systems 

CF6–80C2B Service Bulletin 78–1020, 

Revision 4, dated October 10, 2002. 

(iv) Install new integrated display system 

(IDS) software in six integrated display units 

and three electronic flight information/

engine indication and crew alerting system 

(EICAS) interface units, per the 

Accomplishment Instructions of Boeing 

Service Bulletin 747–31–2242, dated April 

18, 1996. Where the service bulletin specifies 

installation of IDS software version 995–

0017–012, installation of IDS software 

version 995–0017–013, 995–0017–014, 995–

0017–015, 995–0017–016, 995–0017–018, 

3174–COL–EG5–01, 3177–COL–EG5–02, or 

3176–COL–EG5–03 is also acceptable for 

compliance with this paragraph. 

(v) Replace two central maintenance 

computers (CMC), part number 622–8592–

103, with new, improved CMCs, part number 

622–8592–105, and install new software for 

the CMCs, per the Accomplishment 

Instructions of Boeing Service Bulletin 747–

45–2016, Revision 1, dated May 2, 1996. 

Where the service bulletin specifies 

installation of CMC software version 685–

2270–009, installation of CMC software 

version 685–2270–010, or 685–2270–011 is 

also acceptable for compliance with this 

paragraph. 

Repetitive Tests 

(e) For airplanes on which a TRAS lock is 

installed on the thrust reversers: Within 

1,000 flight hours after the installation of the 

TRAS lock, or within 90 flight hours after the 

effective date of this AD, whichever is later, 

do a functional test of the TRAS lock (also 

called an electromechanical lock or brake) 

per the Accomplishment Instructions of 

Boeing Alert Service Bulletin 747–78A2166, 

Revision 2, dated March 15, 2001. Then, 

repeat this test at least every 1,000 flight 

hours. If the functional test cannot be 

successfully performed, before further flight, 

repair per the Accomplishment Instructions 

of the service bulletin, and repeat the test 

until it is successful. 

51442 Federal Register / Vol. 68, No. 166 / Wednesday, August 27, 2003 / Rules and Regulations 

Dispatch Limitations 

(f) If, prior to accomplishment of Boeing 

Service Bulletin 747–78–2151 on any 

airplane, it becomes necessary to install a 

thrust reverser with the TRAS lock installed, 

dispatch of the airplane is allowed per the 

provisions and limitations specified in the 

747–400 Master Minimum Equipment List 

(MMEL), provided that the thrust reverser 

assembly that has the TRAS lock installed is 

deactivated per the 747–400 Dispatch 

Deviations Guide, Boeing Document 

D6U10151, dated June 28, 2002. Installation 

of a thrust reverser without a TRAS lock 

installed and reactivation of the thrust 

reverser must be accomplished within the 

time constraints specified in the MMEL. 

(g) If, after accomplishment of Boeing 

Service Bulletin 747–78–2151 on any 

airplane, it becomes necessary to install a 

thrust reverser assembly that does not have 

the TRAS lock installed, dispatch of the 

airplane is allowed per the provisions and 

limitations specified in the Boeing Model 

747–400 MMEL, provided that the thrust 

reverser assembly that does not have the 

TRAS lock installed is deactivated per the 

747–400 Dispatch Deviations Guide, Boeing 

Document D6U10151, dated June 28, 2002. 

Installation of a thrust reverser with the 

TRAS lock installed and reactivation of the 

thrust reverser must be accomplished within 

the time constraints specified in the MMEL. 

Alternative Methods of Compliance 

(h)(1) An alternative method of compliance 

or adjustment of the compliance time that 

provides an acceptable level of safety may be 

used if approved by the Manager, Seattle 

Aircraft Certification Office (ACO), FAA. 

Operators shall submit their requests through 

an appropriate FAA Principal Maintenance 

Inspector, who may add comments and then 

send it to the Manager, Seattle ACO.

(2) Alternative methods of compliance, 

approved previously in accordance with AD 

2000–09–03, amendment 39–11711, are not 

considered to be approved as alternative 

methods of compliance with this AD.

Note 4: Information concerning the 

existence of approved alternative methods of 

compliance with this AD, if any, may be 

obtained from the Seattle ACO.

Special Flight Permits 

(i) Special flight permits may be issued in 

accordance with sections 21.197 and 21.199 

of the Federal Aviation Regulations (14 CFR 

21.197 and 21.199) to operate the airplane to 

a location where the requirements of this AD 

can be accomplished. 

Incorporation by Reference 

(j) Unless otherwise provided by this AD, 

the actions shall be done in accordance with 

the service bulletins listed in Table 1 of this 

AD, as applicable:

TABLE 1.—APPLICABLE SERVICE BULLETINS

Service bulletin Revision Date 

Boeing Service Bulletin 747–31–2242 .................................................................................................... original ................... April 18, 1996. 

Boeing Service Bulletin 747–45–2016 .................................................................................................... 1 ............................. May 2, 1996. 

Boeing Service Bulletin 747–78–2132 .................................................................................................... 2 ............................. December 11, 

1997. 

Boeing Service Bulletin 747–78–2151, as revised by ............................................................................ 1 ............................. August 21, 1997. 

Notice of Status Change 747–78–2151 NSC 04 and ............................................................................ NSC 04 .................. November 26,

1997. 

Notice of Status Change 747–78–2151 NSC 05 ................................................................................... NSC 05 .................. December 18, 1997 

. 

Boeing Service Bulletin 747–78–2151 .................................................................................................... 2 ............................. January 13, 2000. 

Boeing Service Bulletin 747–78A2113 ................................................................................................... 2 ............................. June 8, 1995. 

Boeing Service Bulletin 747–78A2113 ................................................................................................... 3 ............................. September 11, 

1997. 

Boeing Service Bulletin 747–78A2166 ................................................................................................... 1 ............................. October 9, 1997. 

Boeing Alert Service Bulletin 747–78A2166 ........................................................................................... 2 ............................. March 15, 2001. 

Lockheed Martin Service Bulletin 78–1007 ............................................................................................ 1 ............................. March 18, 1997. 

Middle River Aircraft Systems Service Bulletin 78–1007 ....................................................................... 2 ............................. March 10, 1998. 

Lockheed Martin Service Bulletin 78–1020 ............................................................................................ 2 ............................. March 20, 1997. 

Middle River Aircraft Systems Service Bulletin 78–1020 ....................................................................... 3 ............................. March 16, 1998. 

Middle River Aircraft Systems CF6–80C2B Service Bulletin 78–1020 .................................................. 4 ............................. October 10, 2002. 

Middle River Aircraft Systems CF6–80C2B 

Service Bulletin 78–1020, Revision 4, dated 

October 10, 2002, contains the following list 

of effective pages:

Page No. 

Revision 

level shown

on page 

Date shown on 

page 

1, 7, 20 ................................................................................................................................................................ 4 October 10, 2002. 

2–6, 8–19, 21–37 ................................................................................................................................................ 3 March 16, 1998. 

(1) The incorporation by reference of the 

service bulletins in Table 2 of this AD is 

approved by the Director of the Federal 

Register in accordance with 5 U.S.C. 552(a) 

and 1 CFR part 51. Table 2 follows:

TABLE 2.—SERVICE BULLETINS INCORPORATED BY REFERENCE

Service bulletin Revision Date 

Boeing Service Bulletin 747–31–2242 .................................................................................................... original ................... April 18, 1996. 

Boeing Service Bulletin 747–45–2016 .................................................................................................... 1 ............................. May 2, 1996. 

Boeing Service Bulletin 747–78–2132 .................................................................................................... 2 ............................. December 11, 

1997. 

Boeing Service Bulletin 747–78–2151, as revised by ............................................................................ 1 ............................. August 21, 1997. 

Federal Register / Vol. 68, No. 166 / Wednesday, August 27, 2003 / Rules and Regulations 51443

TABLE 2.—SERVICE BULLETINS INCORPORATED BY REFERENCE—Continued

Service bulletin Revision Date 

Notice of Status Change 747–78–2151 NSC 04 and ............................................................................ NSC 04 .................. November 26,

1997. 

Notice of Status Change 747–78–2151 NSC 05 ................................................................................... NSC 05 .................. December 18, 

1997. 

Boeing Service Bulletin 747–78–2151 .................................................................................................... 2 ............................. January 13, 2000. 

Boeing Alert Service Bulletin 747–78A2166 ........................................................................................... 2 ............................. March 15, 2001. 

Middle River Aircraft Systems CF6–80C2B Service Bulletin 78–1020 .................................................. 4 ............................. October 10, 2002. 

(2) The incorporation by reference of the 

service bulletins in Table 3 of this AD was 

approved previously by the Director of the 

Federal Register as of September 6, 2000 (65 

FR 47252, August 2, 2000). Table 3 follows:

TABLE 3.—SERVICE BULLETINS PREVIOUSLY INCORPORATED BY REFERENCE

Service bulletin 

Revision 

Date 

Lockheed Martin Service Bulletin 78–1007 ...................................................................................................................... 1 March 18, 1997. 

Middle River Aircraft Systems Service Bulletin 78–1007 ................................................................................................. 2 March 10, 1998. 

Lockheed Martin Service Bulletin 78–1020 ...................................................................................................................... 2 March 20, 1997. 

Middle River Aircraft Systems Service Bulletin 78–1020 ................................................................................................. 3 March 16, 1998. 

(3) The incorporation by reference of 

Boeing Service Bulletin 747–78A2113, 

Revision 2, dated June 8, 1995; and Boeing 

Service Bulletin 747–78A2113, Revision 3, 

dated September 11, 1997; was approved 

previously by the Director of the Federal 

Register as of March 13, 2000 (65 FR 5742, 

February 7, 2000). 

(4) The incorporation by reference of 

Boeing Service Bulletin 747–78A2166, 

Revision 1, dated October 9, 1997; was 

approved previously by the Director of the 

Federal Register as of August 25, 1999 (64 FR 

39003, July 21, 1999). 

(5) Copies may be obtained from Boeing 

Commercial Airplane Group, P.O. Box 3707, 

Seattle, Washington 98124–2207; and 

Distribution, Lockheed Martin Technical 

Services, 1330 Kemper Meadow Drive, suite 

110–C, Cincinnati, Ohio 45240. Copies may 

be inspected at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue, SW., Renton, 

Washington; or at the Office of the Federal 

Register, 800 North Capitol Street, NW., suite 

700, Washington, DC. 

Effective Date 

(k) This amendment becomes effective on 

October 1, 2003.

Appendix 1—Thrust Reverser CDU 

Cone Brake Test 

1. This procedure contains steps to do a 

check of the holding torque of the CDU cone 

brake. 

2. CDU cone brake check (Figure 1): 

A. Prepare to do the check: 

(1) Open the fan cowl panels. 

(2) Pull up on the manual release handle 

to unlock the electro-mechanical brake. 

(3) Pull the manual brake release lever on 

the CDU to release the cone brake.

Note: This will release the pre-load tension 

that may occur during a stow cycle.

(4) Return the manual brake release lever 

to the locked position to engage the cone 

brake. 

(5) Remove the two bolts that hold the 

lockout plate to the CDU and remove the 

lockout plate. 

(6) Install a 1⁄4-inch drive and a dial-type 

torque wrench into the CDU drive pad. 

Caution: Do not use more than 100 poundinches of torque when you do this check. 

Excessive torque will damage the CDU. 

(7) Turn the torque wrench to try to 

manually extend the translating cowl until 

you get at least 15 pound-inches.

Note: The cone brake prevents movement 

in the extend direction only. If you try to 

measure the holding torque in the retract 

direction, you will get a false reading.

(8) If the torque is less than 15 poundinches, you must replace the CDU. 

(9) Reinstall the lockout plate. 

B. Return the airplane to its usual 

condition: 

(1) Fully retract the thrust reverser (unless 

already accomplished). 

(2) Pull down on the manual release 

handle on the electro-mechanical brake until 

the handle fully engages the retaining clip 

(unless already accomplished).

Note: This will lock the electro-mechanical 

brake.

(3) Close the fan cowl panels.

BILLING CODE 4910–13–P

51444 Federal Register / Vol. 68, No. 166 / Wednesday, August 27, 2003 / Rules and Regulations 


ER27AU03.002</GPH>
Federal Register / Vol. 68, No. 166 / Wednesday, August 27, 2003 / Rules and Regulations 51445

Issued in Renton, Washington, on August 

13, 2003. 

Neil D. Schalekamp, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service.

[FR Doc. 03–21151 Filed 8–26–03; 8:45 am] 

BILLING CODE 4910–13–C

DEPARTMENT OF HEALTH AND 

HUMAN SERVICES

Food and Drug Administration

21 CFR Part 520

Oral Dosage Form New Animal Drugs; 

Moxidectin Gel

AGENCY: Food and Drug Administration, 

HHS.

ACTION: Final rule, technical 

amendment.

SUMMARY: The Food and Drug 

Administration (FDA) is amending the 

animal drug regulations to reflect 

approval of a supplemental new animal 

drug application (NADA) filed by Fort 

Dodge Animal Health, Division of 

Wyeth. The supplemental NADA adds 

an age precaution to labeling for 

moxidectin gel used for the control of 

various species of internal parasites in 

horses and ponies.

DATES: This rule is effective August 27, 

2003.

FOR FURTHER INFORMATION CONTACT:

Melanie R. Berson, Center for Veterinary 

Medicine (HFV–110), Food and Drug 

Administration, 7500 Standish Pl., 

Rockville, MD 20855; tel: 301–827–

7543; e-mail: mberson@cvm.fda.gov.

SUPPLEMENTARY INFORMATION: Fort 

Dodge Animal Health, Division of 

Wyeth, 800 Fifth St. NW., Fort Dodge, 

IA 50501, filed a supplement to NADA 

141–087 for QUEST (moxidectin) 2.0% 

Equine Oral Gel used for the control of 

various species of internal parasites in 

horses and ponies. The supplemental 

NADA adds a precaution to labeling that 

the product is for oral use in horses and 

ponies 6 months of age and older. The 

supplemental NADA is approved as of 

May 29, 2003, and the regulations are 

amended in 21 CFR 520.1452 to reflect 

the approval and to reflect current 

format. The basis of approval is 

discussed in the freedom of information 

summary.

In accordance with the freedom of 

information provisions of 21 CFR part 

20 and 21 CFR 514.11(e)(2)(ii), a 

summary of safety and effectiveness 

data and information submitted to 

support approval of this application 

may be seen in the Dockets Management 

Branch (HFA–305), Food and Drug 

Administration, 5630 Fishers Lane, rm. 

1061, Rockville, MD 20852, between 9 

a.m. and 4 p.m., Monday through 

Friday.

The agency has determined under 21 

CFR 25.33(d)(1) that this action is of a 

type that does not individually or 

cumulatively have a significant effect on 

the human environment. Therefore, 

neither an environmental assessment 

nor an environmental impact statement 

is required.

This rule does not meet the definition 

of ‘‘rule’’ in 5 U.S.C. 804(3)(A) because 

it is a rule of ‘‘particular applicability.’’

Therefore, it is not subject to the 

congressional review requirements in 5 

U.S.C. 801–808.

List of Subjects in 21 CFR Part 520

Animal drugs.

■ Therefore, under the Federal Food, 

Drug, and Cosmetic Act and under 

authority delegated to the Commissioner 

of Food and Drugs and redelegated to the 

Center for Veterinary Medicine, 21 CFR 

part 520 is amended as follows:

PART 520—ORAL DOSAGE FORM 

NEW ANIMAL DRUGS

■ 1. The authority citation for 21 CFR 

part 520 continues to read as follows:

Authority: 21 U.S.C. 360b.

■ 2. Section 520.1452 is amended by 

revising paragraphs (a), (d)(3), and by 

adding paragraph (c) to read as follows:

§ 520.1452 Moxidectin gel. 

(a) Specifications. Each milliliter of 

gel contains 20 milligrams (2 percent) 

moxidectin.

* * * * *

(c) Special considerations. See 

§ 500.25 of this chapter.

(d) * * *

(3) Limitations. For oral use in horses 

and ponies 6 months of age and older. 

Not for use in horses and ponies 

intended for food.

Dated: August 13, 2003.

Steven D. Vaughn,

Director, Office of New Animal Drug 

Evaluation, Center for Veterinary Medicine.

[FR Doc. 03–21834 Filed 8–27–03; 8:45 am]

BILLING CODE 4160–01–S

DEPARTMENT OF HEALTH AND 

HUMAN SERVICES

Food and Drug Administration

21 CFR Part 520

Oral Dosage Form New Animal Drugs; 

Moxidectin and Praziquantel Gel

AGENCY: Food and Drug Administration, 

HHS.

ACTION: Final rule.

SUMMARY: The Food and Drug 

Administration (FDA) is amending the 

animal drug regulations to reflect 

approval of a new animal drug 

application (NADA) filed by Fort Dodge 

Animal Health, Division of Wyeth. The 

NADA provides for use of a moxidectin 

and praziquantel oral gel for the 

treatment and control of various species 

of internal parasites in horses and 

ponies.

DATES: This rule is effective August 27, 

2003.

FOR FURTHER INFORMATION CONTACT:

Melanie R. Berson, Center for Veterinary 

Medicine (HFV–110), Food and Drug 

Administration, 7500 Standish Pl., 

Rockville, MD 20855; 301–827–7543; email: mberson@cvm.fda.gov.

SUPPLEMENTARY INFORMATION: Fort 

Dodge Animal Health, Div. of Wyeth, 

800 Fifth St. NW., Fort Dodge, IA 50501, 

filed NADA 141–216 for QUEST PLUS 

(moxidectin 2.0%/praziquantel 12.5%) 

Gel for the treatment and control of 

various species of internal parasites in 

horses and ponies. The NADA is 

approved as of May 14, 2003, and part 

520 (21 CFR part 520) is amended by 

adding new § 520.1453 to reflect the 

approval. The basis of approval is 

discussed in the freedom of information 

summary.

In accordance with the freedom of 

information provisions of 21 CFR part 

20 and 21 CFR 514.11(e)(2)(ii), a 

summary of safety and effectiveness 

data and information submitted to 

support approval of this application 

may be seen in the Dockets Management 

Branch (HFA–305), Food and Drug 

Administration, 5630 Fishers Lane, rm. 

1061, Rockville, MD 20852, between 9 

a.m. and 4 p.m., Monday through 

Friday.

Under section 512(c)(2)(F)(ii) of the 

Federal Food, Drug, and Cosmetic Act 

(21 U.S.C. 360b(c)(2)(F)(ii)), this 

approval qualifies for 3 years of 

marketing exclusivity beginning.

The agency has determined under 21 

CFR 25.33(d)(1) that this action is of a 

type that does not individually or 

cumulatively have a significant effect on 

the human environment. Therefore,