51002 Federal Register / Vol. 69, No. 158 / Tuesday, August 17, 2004 / Rules and Regulations 

1The primary, secondary, and seasonal credit 

rates described in this section apply to both 

advances and discounts made under the primary, 

secondary, and seasonal credit programs, 

respectively.

PART 201—EXTENSIONS OF CREDIT 

BY FEDERAL RESERVE BANKS 

(REGULATION A)

■ 1. The authority citation for part 201 

continues to read as follows:

Authority: 12 U.S.C. 248(i)–(j), 343 et seq.,

347a, 347b, 347c, 348 et seq., 357, 374, 374a, 

and 461.

■ 2. In § 201.51, paragraphs (a) and (b) 

are revised to read as follows:

§ 201.51 Interest rates applicable to credit 

extended by a Federal Reserve Bank.1

(a) Primary credit. The interest rates 

for primary credit provided to 

depository institutions under § 201.4(a) 

are:

Federal Reserve 

Bank Rate Effective 

Boston ................ 2.50 Aug. 10, 2004. 

New York ........... 2.50 Aug. 10, 2004. 

Philadelphia ........ 2.50 Aug. 10, 2004. 

Cleveland ........... 2.50 Aug. 10, 2004. 

Richmond ........... 2.50 Aug. 10, 2004. 

Atlanta ................ 2.50 Aug. 10, 2004. 

Chicago .............. 2.50 Aug. 10, 2004. 

St. Louis ............. 2.50 Aug. 11, 2004. 

Minneapolis ........ 2.50 Aug. 10, 2004. 

Kansas City ........ 2.50 Aug. 10, 2004. 

Dallas ................. 2.50 Aug. 10, 2004. 

San Francisco .... 2.50 Aug. 10, 2004. 

(b) Secondary credit. The interest 

rates for secondary credit provided to 

depository institutions under 201.4(b) 

are:

Federal Reserve 

Bank Rate Effective 

Boston ................ 3.00 Aug. 10, 2004. 

New York ........... 3.00 Aug. 10, 2004. 

Philadelphia ........ 3.00 Aug. 10, 2004. 

Cleveland ........... 3.00 Aug. 10, 2004. 

Richmond ........... 3.00 Aug. 10, 2004. 

Atlanta ................ 3.00 Aug. 10, 2004. 

Chicago .............. 3.00 Aug. 10, 2004. 

St. Louis ............. 3.00 Aug. 11, 2004. 

Minneapolis ........ 3.00 Aug. 10, 2004. 

Kansas City ........ 3.00 Aug. 10, 2004. 

Dallas ................. 3.00 Aug. 10, 2004. 

San Francisco .... 3.00 Aug. 10, 2004. 

* * * * *

By order of the Board of Governors of the 

Federal Reserve System, August 11, 2004. 

Jennifer J. Johnson, 

Secretary of the Board.

[FR Doc. 04–18754 Filed 8–16–04; 8:45 am] 

BILLING CODE 6210–02–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. 2002–NM–186–AD; Amendment 

39–13768; AD 2004–16–12] 

RIN 2120–AA64 

Airworthiness Directives; Boeing 

Model 767–200, –300, and –300F Series 

Airplanes

AGENCY: Federal Aviation 

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment supersedes 

three existing airworthiness directives 

(AD); applicable to certain Boeing 

Model 767–200, –300, and –300F series 

airplanes. One AD currently requires 

modification of the nacelle strut and 

wing structure for certain Boeing Model 

767–200, —300, and —300F series 

airplanes powered by Pratt & Whitney 

engines. The second AD currently 

requires a similar modification for 

certain Boeing Model 767–200, –300, 

and –300F series airplanes powered by 

General Electric engines. The third AD 

currently requires repetitive inspections 

for cracking of the outboard pitch load 

fittings of the wing front spar, and 

corrective action if necessary, for certain 

Boeing Model 767–200 series airplanes. 

The third AD also provides a 

terminating action for the repetitive 

inspections, which is optional for 

uncracked pitch load fittings. This 

amendment requires, for airplanes 

subject to the first and second existing 

ADs on which certain modifications 

have been accomplished previously, 

reworking the aft pitch load fitting, and 

installing a new diagonal brace fuse pin. 

This amendment also requires, for 

airplanes subject to the third existing 

AD, replacing the outboard pitch load 

fitting of the wing front spar with a new, 

improved fitting, which terminates 

certain currently required repetitive 

inspections. The actions specified by 

this amendment are intended to prevent 

fatigue cracking in primary strut 

structure, which could result in 

separation of the strut and engine from 

the airplane. This action is intended to 

address the identified unsafe condition.

DATES: Effective September 21, 2004. 

The incorporation by reference of 

certain publications listed in the 

regulations is approved by the Director 

of the Federal Register as of September 

21, 2004. 

The incorporation by reference of 

Boeing Service Bulletin 767–57A0070, 

Revision 1, dated November 16, 2000, 

was approved previously by the Director 

of the Federal Register as of May 14, 

2001 (66 FR 21069, April 27, 2001). 

The incorporation by reference of 

Boeing Service Bulletin 767–54–0081, 

dated July 29, 1999, was approved 

previously by the Director of the Federal 

Register as of May 7, 2001 (66 FR 17492, 

April 2, 2001). 

The incorporation by reference of 

certain publications, as listed in the 

regulations, was approved previously by 

the Director of the Federal Register as of 

March 5, 2001 (66 FR 8085, January 29, 

2001). 

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 October 17, 2000 (65 FR 

58641, October 2, 2000). 

The incorporation by reference of 

Boeing Service Bulletin 767-57-0053, 

Revision 2, dated September 23, 1999, 

was approved previously by the Director 

of the Federal Register as of July 24, 

2000 (65 FR 37843, June 19, 2000).

ADDRESSES: The service information 

referenced in this AD may be obtained 

from Boeing Commercial Airplanes, 

P.O. Box 3707, Seattle, Washington 

98124–2207. 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 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/

code_of_federal_regulations/

ibr_locations.html.

FOR FURTHER INFORMATION CONTACT:

Suzanne Masterson, Aerospace 

Engineer, Airframe Branch, ANM–120S, 

FAA, Seattle Aircraft Certification 

Office, 1601 Lind Avenue, SW., Renton, 

Washington 98055–4056; telephone 

(425) 917–6441; fax (425) 917–6590.

SUPPLEMENTARY INFORMATION: A 

proposal to amend part 39 of the Federal 

Aviation Regulations (14 CFR part 39) 

by superseding the following ADs was 

published in the Federal Register on 

February 11, 2004 (69 FR 6587): 

• AD 2001–02–07, amendment 39–

12091 (66 FR 8085, January 29, 2001), 

which is applicable to certain Boeing 

Model 767–200, –300, and –300F series 

airplanes powered by Pratt & Whitney 

engines. 

• AD 2001–06–12, amendment 39–

12159 (66 FR 17492, April 2, 2001), 

applicable to certain Boeing Model 767–

200, –300, and –300F series airplanes 

powered by General Electric engines. 

Federal Register / Vol. 69, No. 158 / Tuesday, August 17, 2004 / Rules and Regulations 51003

• AD 2001–08–23, amendment 39–

12200 (66 FR 21069, April 27, 2001), 

applicable to certain Boeing Model 767–

200 series airplanes. 

The action proposed to continue to 

require modification of the nacelle strut 

and wing structure, as currently 

required by AD 2001–02–07 and AD 

2001–06–12. The action also proposed 

to continue to require repetitive 

inspections for cracking of the outboard 

pitch load fittings of the wing front spar, 

and corrective action if necessary, as 

currently required by AD 2001–08–23. 

The action also proposed to continue to 

provide a terminating action for the 

repetitive inspections, which is optional 

for uncracked pitch load fittings. For 

certain airplanes on which certain 

modifications have been accomplished 

previously, the action proposed to add 

new requirements for reworking the aft 

load pitch fitting, and installing a new 

diagonal brace fuse pin. For certain 

other airplanes, the action proposed to 

add a new requirement for replacing the 

outboard pitch load fitting of the wing 

front spar with a new, improved fitting 

on the left- and right-hand sides of the 

airplane, which would terminate 

repetitive inspections currently required 

by AD 2001–08–23. 

Comments 

Interested persons have been afforded 

an opportunity to participate in the 

making of this amendment. The FAA 

has duly considered the single comment 

received. 

Request To Clarify Required Actions 

The commenter states that the 

Accomplishment Instructions of Boeing 

Service Bulletin 767–54–0081, Revision 

1, dated February 7, 2002, specify 

installing a new pitch load fitting with 

a new part number. The commenter 

states that the Accomplishment 

Instructions do not specify reworking 

the aft load pitch fitting, as stated in the 

‘‘Differences Between Proposed AD and 

Service Bulletins’’ section of the 

proposed AD. The commenter requests 

that we revise the proposed AD to 

clarify that any operator that has 

accomplished the strut improvement 

modification per the original issue of 

Boeing Service Bulletin 767–54–0081, 

dated July 29, 1999, must accomplish 

the additional rework in Boeing Service 

Bulletin 767–54–0081, Revision 1. The 

commenter notes that this is supported 

by ‘‘Note 7 (1)’’ of the proposed AD, 

which indicates that no further action is 

needed if aft pitch load fittings with 

certain part numbers are installed. 

We do not agree with the commenter’s 

statement that the Accomplishment 

Instructions in Revision 1 of the service 

bulletin do not specify reworking the aft 

load pitch fitting. The commenter is 

correct that the Accomplishment 

Instructions do specify installing a new 

pitch load fitting with a new part 

number for airplanes not modified per 

the original issue of the service bulletin. 

However, Paragraph CB. under 

‘‘Additional Work Required—Group 3 

through 12 Airplanes’’ in the 

Accomplishment Instructions of the 

service bulletin specifies reworking the 

affected aft pitch load fitting and 

installing the diagonal brace with a new 

fuse pin for airplanes with an aft pitch 

load fitting with certain part numbers. 

However, we agree that clarifying 

paragraph (l) of this AD would be 

helpful. (We note that the paragraph 

that the commenter identifies as ‘‘Note 

7 (1)’’ is actually paragraph (l) of this 

AD—with a (lower-case) letter ‘‘L,’’ not 

with a number ‘‘1.’’ Paragraph (l) is 

independent from Note 7.) Paragraph (d) 

of this AD requires that strut 

modifications performed after the 

effective date of this AD be done per 

Revision 1 of that service bulletin. The 

requirements of paragraph (l) of this AD 

should apply only to airplanes that have 

been modified before the effective date 

of this AD per the original issue of 

Boeing Service Bulletin 767–54–0081. 

We recognize that the wording in 

paragraph (l) of the proposed AD could 

inadvertently require extra work for any 

operator who accomplished Revision 1 

of the service bulletin before the 

effective date of this AD. This was not 

our intent. Therefore, for clarification, 

we have revised paragraph (l) of this AD 

to apply only to subject airplanes ‘‘on 

which the modification required by 

paragraph (d) of this AD has been 

accomplished per the original issue of 

Boeing Service Bulletin 767–54–0081. 

***’’

Conclusion 

After careful review of the available 

data, including the comment noted 

above, we have determined that air 

safety and the public interest require the 

adoption of the rule as proposed. 

Cost Impact 

There are approximately 619 

airplanes of the affected design in the 

worldwide fleet. We estimate that 255 

airplanes of U.S. registry will be affected 

by this AD. 

The following table shows the 

estimated costs associated with the 

actions currently required by ADs 2001–

02–07, 2001–06–12, and 2001–08–23, at 

an average labor rate of $65 per work 

hour:

ESTIMATED COST IMPACT—ACTIONS CURRENTLY REQUIRED

Actions in Boeing service bulletin 

Number of

affected

U.S.-

registered

airplanes 

Work hours Parts cost Cost per airplane Fleet cost 

76–54–0080 ........................... 86 11,423–1,519 Free ....................................... $92,495–$98,735 $7,954,570–$8,491,210 

767–54–0081 ......................... 169 11,474 Free ....................................... 95,810 16,191,890 

767–54–0069 ......................... 249 106 Free ....................................... 6,890 1,715,610 

767–54–0083 ......................... 228 1 Free ....................................... 65 14,820 

767–54–0088 ......................... 255 2 Free ....................................... 130 33,150 

767–54A0094 ......................... 117 20 Free ....................................... 1,300 152,100 

767–57–0053 ......................... 255 5 None ...................................... 325 82,875 

767–29–0057 ......................... 200 16 Free ....................................... 1,040 208,000 

767–57A0070 ......................... 67 4 None ...................................... 2260 217,420 

1 Including time for gaining access and closing up.) 

2Per inspection cycle. 

For affected airplanes, the new 

inspection to determine the part number 

of the aft load pitch fittings that is 

required by this AD will take 

approximately 1 work hour per airplane 

to accomplish, at an average labor rate 

of $65 per work hour. Based on these 

figures, the cost impact of this 

51004 Federal Register / Vol. 69, No. 158 / Tuesday, August 17, 2004 / Rules and Regulations 

requirement is estimated to be $65 per 

airplane. 

For affected airplanes, the new 

replacement of the outboard pitch load 

fittings that is required by this AD takes 

approximately 14 work hours per 

airplane to accomplish, at an average 

labor rate of $65 per work hour. 

Required parts cost approximately 

$14,438 per airplane. Based on these 

figures, the cost impact of this 

requirement is estimated to be $15,348 

per airplane. 

The cost impact figures discussed 

above are based on assumptions that no 

operator has yet accomplished any of 

the current or proposed 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; however, 

as noted previously, time to gain access 

and close up has been included for 

certain actions in this AD. 

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 amendments 39–12091 (66 FR 

8085, January 29, 2001), 39–12159 (66 

FR 17492, April 2, 2001), and 39–12200 

(66 FR 21069, April 27, 2001); and by 

adding a new airworthiness directive 

(AD), amendment 39–13768, to read as 

follows:

2004–16–12 Boeing: Amendment 39–13768. 

Docket 2002–NM–186–AD. Supersedes 

AD 2001–02–07, Amendment 39–12091; 

AD 2001–06–12, Amendment 39–12159; 

and AD 2001–08–23, Amendment 39–

12200.

Applicability: Model 767–200, –300, and 

–300F series airplanes; certificated in any 

category; line numbers (L/Ns) 1 through 663 

inclusive; powered by Pratt & Whitney or 

General Electric engines. 

Compliance: Required as indicated, unless 

accomplished previously. 

To prevent fatigue cracking in primary 

strut structure, which could result in 

separation of the strut and engine from the 

airplane, accomplish the following: 

Requirements of AD 2001–02–07 

Modifications 

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

series airplanes powered by Pratt & Whitney 

engines, L/Ns 1 through 663 inclusive: When 

the airplane has reached the flight cycle 

threshold as defined by the flight cycle 

threshold formula described in Figure 1 of 

Boeing Service Bulletin 767–54–0080, dated 

October 7, 1999, or Revision 1, dated May 9, 

2002; or within 20 years since the date of 

manufacture; whichever occurs first; modify 

the nacelle strut and wing structure on both 

the left-hand and right-hand sides of the 

airplane, in accordance with the service 

bulletin. Use of the flight cycle threshold 

formula described in Figure 1 of the service 

bulletin is an acceptable alternative to the 20-

year threshold, provided the corrosion 

prevention and control program inspections, 

as described in paragraphs 1 and 2 of Figure 

1, have been met. As of the effective date of 

this AD, only Revision 1 of the service 

bulletin may be used. 

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

series airplanes powered by Pratt & Whitney 

engines, L/Ns 1 through 663 inclusive: Prior 

to or concurrently with the accomplishment 

of the modification of the nacelle strut and 

wing structure required by paragraph (a) of 

this AD; as specified in paragraph 1.D., Table 

2, of Boeing Service Bulletin 767–54–0080, 

dated October 7, 1999, or Revision 1, dated 

May 9, 2002; accomplish the actions 

specified in Boeing Service Bulletins 767–

54–0069, Revision 1, dated January 29, 1998, 

or Revision 2, dated August 31, 2000; 767–

54–0083, dated September 17, 1998; 767–54–

0088, Revision 1, dated July 29, 1999; 767–

54A0094, Revision 1, dated September 16, 

1999, or Revision 2, dated February 7, 2002; 

767–57–0053, Revision 2, dated September 

23, 1999; and 767–29–0057, dated December 

16, 1993, including Notice of Status Change 

NSC 1, dated November 23, 1994; or Revision 

1, dated August 14, 2003; as applicable; in 

accordance with those service bulletins. 

Accomplishment of this paragraph 

constitutes terminating action for the 

repetitive inspections required by AD 94–11–

02, amendment 39–8918; AD 2000–07–05, 

amendment 39–11659; and AD 2000–12–17, 

amendment 39–11795.

Note 1: Paragraph (b) of this AD specifies 

prior or concurrent accomplishment of 

Boeing Service Bulletin 767–57–0053, 

Revision 2, dated September 23, 1999; 

however, Table 2 of Boeing Service Bulletin 

767–54–0080, dated October 7, 1999, 

specifies prior or concurrent accomplishment 

of the original issue of the service bulletin. 

Therefore, accomplishment of the applicable 

actions specified in Boeing Service Bulletin 

767–57–0053, dated June 27, 1996, or 

Revision 1, dated October 31, 1996, prior to 

the effective date of this AD, is considered 

acceptable for compliance with the actions in 

Boeing Service Bulletin 767–57–0053 

required by paragraph (b) of this AD.

Repair 

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

series airplanes powered by Pratt & Whitney 

engines, L/Ns 1 through 663 inclusive: If any 

damage (corrosion or cracking) to the 

airplane structure is found during the 

accomplishment of the modification required 

by paragraph (a) of this AD; and the service 

bulletin specifies to contact Boeing for 

appropriate action: Prior to further flight, 

repair in accordance with a method approved 

by the Manager, Seattle Aircraft Certification 

Office (ACO), FAA; or in accordance with 

data meeting the type certification basis of 

the airplane approved by a Boeing Company 

Designated Engineering Representative (DER) 

who has been authorized by the FAA to make 

such findings. For a repair method to be 

approved by the Manager, Seattle ACO, as 

required by this paragraph, the Manager’s 

approval letter must specifically reference 

this AD. 

Requirements of AD 2001–06–12 

Modification 

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

series airplanes powered by General Electric 

engines, L/Ns 1 through 663 inclusive: 

Modify the nacelle strut and wing structure 

on both the left-hand and right-hand sides of 

the airplane, in accordance with Boeing 

Service Bulletin 767–54–0081, dated July 29, 

1999; or Revision 1, dated February 7, 2002; 

at the later of the times specified in 

paragraphs (d)(1) and (d)(2) of this AD. After 

the effective date of this AD, only Revision 

1 may be used. 

Federal Register / Vol. 69, No. 158 / Tuesday, August 17, 2004 / Rules and Regulations 51005

(1) Prior to the accumulation of 37,500 

total flight cycles, or within 20 years since 

date of manufacture, whichever occurs first. 

Use of the optional threshold formula 

described in Figure 1 of the service bulletin 

is an acceptable alternative to the 20-year 

threshold provided that the conditions 

specified in Figure 1 of the service bulletin 

are met. For the optional threshold formula 

in Figure 1 to be used, actions in the service 

bulletins listed in Item 2 of Figure 1 must be 

accomplished no later than 20 years since the 

airplane’s date of manufacture. 

(2) Within 3,000 flight cycles after May 7, 

2001 (the effective date of AD 2001–06–12). 

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

series airplanes powered by General Electric 

engines, L/Ns 1 through 663 inclusive: Prior 

to or concurrently with the accomplishment 

of the modification of the nacelle strut and 

wing structure required by paragraph (d) of 

this AD; as specified in paragraph 1.D., Table 

2, ‘‘Prior or Concurrent Service Bulletins,’’ of 

Boeing Service Bulletin 767–54–0081, dated 

July 29, 1999; or Revision 1, dated February 

7, 2002; accomplish the actions specified in 

Boeing Service Bulletin 767–29–0057, dated 

December 16, 1993, or Revision 1, dated 

August 14, 2003; Boeing Service Bulletin 

767–54–0069, Revision 1, dated January 29, 

1998, or Revision 2, dated August 31, 2000; 

Boeing Service Bulletin 767–54–0083, dated 

September 17, 1998; Boeing Service Bulletin 

767–54–0088, Revision 1, dated July 29, 

1999; Boeing Service Bulletin 767–54A0094, 

Revision 1, dated September 16, 1999, or 

Revision 2, dated February 7, 2002; and 

Boeing Service Bulletin 767–57–0053, 

Revision 2, dated September 23, 1999; as 

applicable, in accordance with those service 

bulletins.

Note 2: AD 2000–12–17, amendment 39–

11795, requires accomplishment of Boeing 

Service Bulletin 767–57–0053, Revision 2, 

dated September 23, 1999. However, 

inspections and rework accomplished in 

accordance with Boeing Service Bulletin 

767–57–0053, Revision 1, dated October 31, 

1996, are acceptable for compliance with the 

applicable actions required by paragraph (e) 

of this AD.

Note 3: AD 2000–07–05, amendment 39–

11659, requires accomplishment of Boeing 

Service Bulletin 767–54A0094, dated May 

22, 1998. Inspections and rework 

accomplished in accordance with Boeing 

Service Bulletin 767–54A0094, dated May 

22, 1998, are acceptable for compliance with 

the applicable actions required by paragraph 

(e) of this AD.

Note 4: AD 2001–02–07, amendment 39–

12091, requires accomplishment of Boeing 

Service Bulletin 767–54–0069, Revision 1, 

dated January 29, 1998, or Revision 2, dated 

August 31, 2000. Inspections and rework 

accomplished in accordance with those 

service bulletins are acceptable for 

compliance with the applicable actions 

required by paragraph (e) of this AD.

Repairs 

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

series airplanes powered by General Electric 

engines, L/Ns 1 through 663 inclusive: If any 

damage to the airplane structure is found 

during the accomplishment of the 

modification required by paragraph (d) of 

this AD, and the service bulletin specifies to 

contact Boeing for appropriate action, prior 

to further flight, repair in accordance with a 

method approved by the Manager, Seattle 

ACO, or a Boeing Company DER who has 

been authorized by the FAA to make such 

findings. For a repair method to be approved 

by the Manager, Seattle ACO, as required by 

this paragraph, the Manager’s approval letter 

must specifically reference this AD. 

Requirements of AD 2001–08–23

Initial and Repetitive Inspections 

(g) For Model 767–200 series airplanes, as 

listed in Boeing Service Bulletin 767–

57A0070, Revision 1, dated November 16, 

2000: Within 30 days after May 14, 2001 (the 

effective date of AD 2001–08–23, amendment 

39–12200), perform a high frequency eddy 

current (HFEC) inspection for cracking of the 

outboard pitch load fitting of the wing front 

spar, on the left-hand and right-hand sides of 

the airplane, according to Boeing Service 

Bulletin 767–57A0070, Revision 1, dated 

November 16, 2000; Revision 2, dated August 

2, 2001; or Revision 3, dated November 8, 

2001. If no cracking is found, repeat the 

inspection at intervals not to exceed 3,000 

flight cycles or 18 months, whichever occurs 

first, until paragraph (i) or (m) of this AD is 

done.

Note 5: Inspections done prior to the 

effective date of this AD, in accordance with 

Boeing Service Bulletin 767–57A0070, dated 

March 2, 2000, as revised by Information 

Notice 767–57A0070 IN 01, dated March 23, 

2000, are considered acceptable for 

compliance with paragraph (g) of this AD.

Corrective Action 

(h) For Model 767–200 series airplanes, as 

listed in Boeing Service Bulletin 767–

57A0070, Revision 1, dated November 16, 

2000: If any cracking is found during any 

inspection per paragraph (g) of this AD, prior 

to further flight, do paragraph (h)(1) or (h)(2) 

of this AD. 

(1) Rework the cracked outboard pitch load 

fitting according to a method approved by the 

Manager, Seattle ACO, or according to data 

meeting the type certification basis of the 

airplane approved by a Boeing Company DER 

who has been authorized by the Manager, 

Seattle ACO, to make such findings. For a 

rework method to be approved by the 

Manager, Seattle ACO, as required by this 

paragraph, the Manager’s approval letter 

must specifically reference this AD.

(2) Replace the cracked outboard pitch load 

fitting with a new, improved fitting 

(including removing the existing fittings, 

performing an HFEC inspection for damage 

of fastener holes, repairing damaged fastener 

holes, and installing new fittings of improved 

design), according to Boeing Service Bulletin 

767–57A0070, Revision 1, dated November 

16, 2000; Revision 2, dated August 2, 2001; 

or Revision 3, dated November 8, 2001. Such 

replacement terminates the repetitive 

inspections required by paragraph (g) of this 

AD for the replaced fitting.

Note 6: Boeing Service Bulletin 767–

57A0070, Revision 1, refers to Boeing Service 

Bulletin 767–57–0053 as an additional source 

of service information for accomplishment of 

the replacement of the outboard pitch load 

fitting on Model 767–200 series airplanes.

Optional Terminating Action 

(i) For Model 767–200 series airplanes, as 

listed in Boeing Service Bulletin 767–

57A0070, Revision 1, dated November 16, 

2000: Replacement of the outboard pitch load 

fitting of the wing front spar with a new, 

improved fitting, according to Boeing Service 

Bulletin 767–57A0070, Revision 1, dated 

November 16, 2000; Revision 2, dated August 

2, 2001; or Revision 3, dated November 8, 

2001; terminates the repetitive inspections 

required by paragraph (g) of this AD for the 

replaced fitting. 

Spares 

(j) For Model 767–200 series airplanes, as 

listed in Boeing Service Bulletin 767–

57A0070, Revision 1, dated November 16, 

2000: As of May 14, 2001, no one may install 

on any airplane an outboard pitch load fitting 

that has a part number listed in the ‘‘Existing 

Part Number’’ column of Paragraph 2.E. of 

Boeing Service Bulletin 767–57A0070, 

Revision 1, dated November 16, 2000. 

New Requirements of This AD 

Boeing Service Bulletin 767–54–0080, 

Revision 1, Groups 4 Through 10: Inspection 

and Additional Work, if Necessary 

(k) For airplanes listed in Groups 4 through 

10 of Boeing Service Bulletin 767–54–0080, 

Revision 1, dated May 9, 2002, on which the 

modification required by paragraph (a) of this 

AD has been accomplished prior to the 

effective date of this AD: Within 18 months 

after the effective date of this AD, perform an 

inspection of the aft pitch load fitting of the 

wing front spar to determine the part number 

(P/N) of the fitting. 

(1) If the aft pitch load fitting on the lefthand side of the airplane has P/N 112T7005–

57 and the aft pitch load fitting on the righthand side of the airplane has P/N 112T7005–

58: No further action is required by this 

paragraph. 

(2) If the aft pitch load fitting on the lefthand side of the airplane has P/N 112T7005–

53 or the aft pitch load fitting on the righthand side of the airplane has P/N 112T7005–

54: Within 18 months after the effective date 

of this AD, rework the affected aft pitch load 

fitting and install the diagonal brace with a 

new fuse pin, in accordance with Steps E. 

and F. under the heading ‘‘Additional Work 

Required—Group 4 through 10 Airplanes’’ in 

the Accomplishment Instructions of the 

service bulletin.

Note 7: This AD does not require the 

installation of new markers that is specified 

under the heading ‘‘Additional Work 

Required—Group 4 through 10 Airplanes’’ in 

the Accomplishment Instructions of Boeing 

Service Bulletin 767–54–0080, Revision 1, 

dated May 9, 2002.

Boeing Service Bulletin 767–54–0081, 

Revision 1, Groups 3 Through 12: Inspection 

and Additional Work, if Necessary 

(l) For airplanes listed in Groups 3 through 

12 of Boeing Service Bulletin 767–54–0081, 

51006 Federal Register / Vol. 69, No. 158 / Tuesday, August 17, 2004 / Rules and Regulations 

Revision 1, dated February 7, 2002, on which 

the modification required by paragraph (d) of 

this AD has been accomplished per the 

original issue of Boeing Service Bulletin 767–

54–0081, dated July 29, 1999: Within 18 

months after the effective date of this AD, 

perform an inspection of the aft pitch load 

fitting of the wing front spar to determine the 

P/N of the fitting. 

(1) If the aft pitch load fitting on the lefthand side of the airplane has P/N 112T7005–

57 and the aft pitch load fitting on the righthand side of the airplane has P/N 112T7005–

58: No further action is required by this 

paragraph. 

(2) If the aft pitch load fitting on the lefthand side of the airplane has P/N 112T7005–

53 or the aft pitch load fitting on the righthand side of the airplane has P/N 112T7005–

54: Within 18 months after the effective date 

of this AD, rework the affected aft pitch load 

fitting and install the diagonal brace with a 

new fuse pin, in accordance with Steps CB. 

and CC. under the heading ‘‘Additional Work 

Required—Group 3 through 12 Airplanes’’ in 

the Accomplishment Instructions of the 

service bulletin.

Note 8: This AD does not require the 

installation of new markers that is specified 

under the heading ‘‘Additional Work 

Required—Group 3 through 12 Airplanes’’ in 

the Accomplishment Instructions of Boeing 

Service Bulletin 767–54–0081, Revision 1, 

dated February 7, 2002.

L/Ns 1–101 Inclusive: Replacement of 

Outboard Pitch Load Fitting 

(m) For Model 767–200 series airplanes 

having L/Ns 1 through 101 inclusive: At the 

applicable time specified in paragraph (m)(1) 

or (m)(2) of this AD, replace the outboard 

pitch load fitting of the wing front spar, on 

the left- and right-hand sides of the airplane, 

with a new, improved fitting, in accordance 

with the Accomplishment Instructions of 

Boeing Service Bulletin 767–57A0070, 

Revision 1, dated November 16, 2000; 

Revision 2, dated August 2, 2001; or Revision 

3, dated November 8, 2001. Accomplishment 

of this replacement constitutes terminating 

action for the repetitive inspections required 

by paragraph (g) of this AD.

(1) For airplanes on which the 

modification required by paragraph (a) or (d) 

of this AD, as applicable, has not been 

accomplished before the effective date of this 

AD: Do the replacement prior to or 

concurrently with the accomplishment of the 

modification of the nacelle strut and wing 

structure required by paragraph (a) of this 

AD, as specified in paragraph 1.D., Table 2, 

of Boeing Service Bulletin 767–54–0080, 

Revision 1, dated May 9, 2002. 

(2) For airplanes on which the 

modification required by paragraph (a) or (d) 

of this AD, as applicable, has been 

accomplished before the effective date of this 

AD: Do the replacement within 48 months 

after the effective date of this AD. 

Alternative Methods of Compliance 

(n)(1) In accordance with 14 CFR 39.19, the 

Manager, Seattle ACO, is authorized to 

approve alternative methods of compliance 

(AMOCs) for this AD. 

(2) An AMOC that provides an acceptable 

level of safety may be used for a repair 

required by this AD, if it is approved by a 

Boeing Company DER who has been 

authorized by the Manager, Seattle ACO, to 

make such findings. 

(3) AMOCs approved previously per AD 

2001–02–07, amendment 39–12091, are 

approved as alternative methods of 

compliance with the applicable actions in 

paragraphs (a), (b), and (c) of this AD. 

(4) AMOCs approved previously per AD 

2001–06–12, amendment 39–12159, are 

approved as alternative methods of 

compliance with the applicable actions in 

paragraphs (d), (e), and (f) of this AD. 

(5) AMOCs approved previously in 

accordance with AD 2000–12–17, 

amendment 39–11795; AD 2000–07–05, 

amendment 39–11659; AD 2001–02–07, 

amendment 39–12091; and AD 94–11–02, 

amendment 39–8918; are approved as 

alternative methods of compliance with the 

applicable actions in paragraph (e) of this 

AD. 

(6) AMOCs approved previously per AD 

2001–08–23, amendment 39–12200, are 

approved as alternative methods of 

compliance with the applicable actions in 

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

Incorporation by Reference 

(o) Unless otherwise specified in this AD, 

the actions shall be done in accordance with 

the Boeing Service Bulletins listed in Table 

1 of this AD, as applicable.

TABLE 1.—BOEING SERVICE BULLETINS INCORPORATED BY REFERENCE

Service bulletin Revision Date 

767–29–0057 ..................................................................................................... Original ...................................................... December 16, 1993. 

767–29–0057 NSC 1 ......................................................................................... Original ...................................................... November 23, 1994. 

767–29–0057 ..................................................................................................... 1 ................................................................. August 14, 2003. 

767–54–0069 ..................................................................................................... 1 ................................................................. January 29, 1998. 

767–54–0069 ..................................................................................................... 2 ................................................................. August 31, 2000. 

767–54–0080 ..................................................................................................... Original ...................................................... October 7, 1999. 

767–54–0080, Including Appendices A, B, and C ............................................ 1 ................................................................. May 9, 2002. 

767–54–0081 ..................................................................................................... Original ...................................................... July 29, 1999. 

767–54–0081, Including Appendices A, B, C, and D ....................................... 1 ................................................................. February 7, 2002. 

767–54–0083 ..................................................................................................... Original ...................................................... September 17, 1998. 

767–54–0088 ..................................................................................................... 1 ................................................................. July 29, 1999. 

767–54A0094 .................................................................................................... 1 ................................................................. September 16, 1999. 

767–54A0094 .................................................................................................... 2 ................................................................. February 7, 2002. 

767–57–0053 ..................................................................................................... 2 ................................................................. September 23, 1999. 

767–57A0070 .................................................................................................... 1 ................................................................. November 16, 2000. 

767–57A0070 .................................................................................................... 2 ................................................................. August 2, 2001. 

767–57A0070 .................................................................................................... 3 ................................................................. November 8, 2001. 

(1) The incorporation by reference of the 

Boeing 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.—NEW BOEING SERVICE BULLETINS INCORPORATED BY REFERENCE

Service bulletin Revision Date 

767–29–0057 ......................................................................... 1 ............................................................................................ August 14, 2003. 

767–54–0080, Including Appendices A, B, and C ................ 1 ............................................................................................ May 9, 2002. 

767–54–0081, Including Appendices A, B, C, and D ........... 1 ............................................................................................ February 7, 2002. 

767–54A0094 ......................................................................... 2 ............................................................................................ February 7, 2002. 

767–57A0070 ......................................................................... 2 ............................................................................................ August 2, 2001. 

Federal Register / Vol. 69, No. 158 / Tuesday, August 17, 2004 / Rules and Regulations 51007

TABLE 2.—NEW BOEING SERVICE BULLETINS INCORPORATED BY REFERENCE—Continued

Service bulletin Revision Date 

767–57A0070 ......................................................................... 3 ............................................................................................ November 8, 2001. 

(2) The incorporation by reference of 

Boeing Service Bulletin 767–57A0070, 

Revision 1, dated November 16, 2000, was 

approved previously by the Director of the 

Federal Register as of May 14, 2001 (66 FR 

21069), April 27, 2001). 

(3) The incorporation by reference of 

Boeing Service Bulletin 767–54–0081, dated 

July 29, 1999, was approved previously by 

the Director of the Federal Register as of May 

7, 2001 (66 FR 17492, April 2, 2001). 

(4) The incorporation by reference of the 

Boeing Service Bulletins in Table 3 of this 

AD was approved previously by the Director 

of the Federal Register as of March 5, 2001 

(66 FR 8085, January 29, 2001).

TABLE 3.—BOEING SERVICE BULLETINS PREVIOUSLY INCORPORATED BY REFERENCE

Service bulletin Revision Date 

767–29–0057 NSC 1 ............................................................. Original .................................................................................. November 23, 1994. 

767–54–0080 ......................................................................... Original .................................................................................. October 7, 1999. 

767–54–0069 ......................................................................... 2 ............................................................................................ August 31, 2000. 

767–54A0094 ......................................................................... 1 ............................................................................................ September 16, 1999. 

(5) The incorporation by reference of the 

Boeing Service Bulletins in Table 4 of this 

AD was approved previously by the Director 

of the Federal Register as of October 17, 2000 

(65 FR 58641, October 2, 2000).

TABLE 4.—BOEING SERVICE BULLETINS PREVIOUSLY INCORPORATED BY REFERENCE

Service bulletin Revision Date 

767–29–0057 ......................................................................... Original .................................................................................. December 16, 1993. 

767–54–0069 ......................................................................... 1 ............................................................................................ January 29, 1998. 

767–54–0083 ......................................................................... Original .................................................................................. September 17, 1998. 

767–54–0088 ......................................................................... 1 ............................................................................................ July 29, 1999. 

(6) The incorporation by reference of 

Boeing Service Bulletin 767–57–0053, 

Revision 2, dated September 23, 1999, was 

approved previously by the Director of the 

Federal Register as of July 24, 2000 (65 FR 

37843, June 19, 2000). 

(7) Copies may be obtained from Boeing 

Commercial Airplanes, P.O. Box 3707, 

Seattle, Washington 98124–2207. Copies may 

be inspected 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/

code_of_federal_regulations/

ibr_locations.html. 

Effective Date 

(p) This amendment becomes effective on 

September 21, 2004.

Issued in Renton, Washington, on July 29, 

2004. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service.

[FR Doc. 04–17984 Filed 8–16–04; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF HOMELAND 

SECURITY 

Customs and Border Protection 

19 CFR Part 123 

Required Advance Electronic 

Presentation of Cargo Information: 

Compliance Dates for Truck Carriers

AGENCY: Customs and Border Protection, 

DHS.

ACTION: Announcement of compliance 

dates. 

SUMMARY: This document informs truck 

carriers when they will be required to 

transmit advance electronic cargo 

information to Customs and Border 

Protection regarding cargo they are 

bringing into the United States, as 

mandated by section 343(a) of the Trade 

Act of 2002 and the implementing 

regulations. The dates when truck 

carriers will be required to comply vary 

depending on the port of entry at which 

the truck carrier will be arriving in the 

United States.

DATES: The implementation schedule set 

forth in the SUPPLEMENTARY INFORMATION

discussion specifies three compliance 

dates, depending on the location of the 

port of entry.

FOR FURTHER INFORMATION CONTACT: For 

questions concerning Inbound Truck 

Cargo: James Swanson, Field 

Operations, (202) 344–2576.

SUPPLEMENTARY INFORMATION: 

Background 

Section 343(a) of the Trade Act of 

2002, as amended (the Act; 19 U.S.C. 

2071 note), required that Customs and 

Border Protection (CBP) promulgate 

regulations providing for the mandatory 

collection of electronic cargo 

information, by way of a CBP-approved 

electronic data interchange system, 

before the cargo is brought into or 

departs the United States by any mode 

of commercial transportation (sea, air, 

rail or truck). The cargo information 

required is that which is reasonably 

necessary to enable high-risk shipments 

to be identified for purposes of ensuring 

cargo safety and security and preventing 

smuggling pursuant to the laws enforced 

and administered by CBP. 

On December 5, 2003, CBP published 

in the Federal Register (68 FR 68140) a 

final rule intended to effectuate the 

provisions of the Act. In particular, a 

new § 123.92 (19 CFR 123.92) was