[Federal Register Volume 70, Number 23 (Friday, February 4, 2005)]
[Rules and Regulations]
[Pages 5917-5920]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 05-1805]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2004-19201; Directorate Identifier 2003-NM-100-AD; 
Amendment 39-13959; AD 2005-03-03]
RIN 2120-AA64


Airworthiness Directives; Boeing Model 767-200, -300, and -300F 
Series Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule.

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SUMMARY: The FAA is superseding an existing airworthiness directive 
(AD), which applies to all Boeing Model 767-200, -300, and -300F series 
airplanes. That AD currently requires examination of maintenance 
records to determine if Titanine JC5A (also known as Desoto 823E508) 
corrosion inhibiting compound (``C.I.C.'') was ever used; inspection 
for cracks or corrosion and corrective action, if applicable; 
repetitive inspections and C.I.C. applications; and modification of the 
aft trunnion area of the outer cylinder, which terminates the need for 
the repetitive inspections and C.I.C. applications. This new AD also 
requires, for certain other airplanes, repetitive inspections for 
cracks or corrosion, corrective action if necessary, and repetitive 
C.I.C. applications. This AD is prompted by a report that JC5A was used 
on more airplanes during production than previously identified. We are 
issuing this AD to prevent severe corrosion in the main landing gear 
(MLG) outer cylinder at the aft trunnion, which could develop into 
stress corrosion cracking and consequent collapse of the MLG.

DATES: This AD becomes effective March 11, 2005.
    The incorporation by reference of a certain publication listed in 
the AD is approved by the Director of the Federal Register as of March 
11, 2005.
    On May 6, 2002 (67 FR 19322, April 19, 2002), the Director of the 
Federal Register approved the incorporation by reference of a certain 
other publication.

ADDRESSES: For service information identified in this AD, contact 
Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124-
2207. You can examine this information 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.
    Docket: The AD docket contains the proposed AD, comments, and any 
final disposition. You can 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 U.S. 
Department of Transportation, 400 Seventh Street, SW., room PL-401, 
Washington, DC. This docket number is FAA-2004-19201; the directorate 
identifier for this docket is 2003-NM-100-AD.

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: The FAA proposed to amend part 39 of the 
Federal Aviation Regulations (14 CFR part 39) with an AD to supersede 
AD 2002-08-07, amendment 39-12715, (67 FR 19322, April 19, 2002). The 
existing AD applies to all Boeing Model 767-200, -300, and -00F series 
airplanes. The proposed AD was published in the Federal Register on 
September 29, 2004 (69 FR 58103). That action proposed to continue to 
require examination of maintenance records to determine if Titanine 
JC5A (also known as Desoto 823E508) corrosion inhibiting compound 
(``C.I.C.'') was ever used; inspection for cracks or corrosion and 
corrective action, if applicable; repetitive inspections and C.I.C. 
applications; and modification of the aft trunnion area of the outer 
cylinder, which terminates the need for the repetitive inspections and 
C.I.C. applications. The action also proposed to require, for certain 
other airplanes, repetitive inspections for cracks or corrosion, 
corrective action if necessary, and repetitive C.I.C. applications.

Comments

    We provided the public the opportunity to participate in the 
development of this AD. We have considered the comments that have been 
submitted on the proposed AD.

Support for the Proposed AD

    One commenter supports the proposed AD.

Request To Add Compliance Statement

    One commenter requests that we add the verbiage, ``required as 
indicated, unless accomplished previously,'' to the compliance section 
of the proposed AD. The commenter believes this statement is needed to 
obtain credit for the inspections and repetitive C.I.C applications it 
accomplished, prior to issuance of the proposed AD, on its airplanes in 
accordance with Boeing Alert Service Bulletin 767-32A0192, Revision 1, 
dated March 13, 2003.
    We partially agree, since similar language to that suggested by the 
commenter is found in paragraph (e) of this AD. As part of our effort 
to use plain language in ADs, we have rewritten the compliance 
statement as follows: ``You are responsible for having the actions 
required by this AD performed within the compliance times specified, 
unless the actions have already been done.'' While the language has 
changed, the intent of the statement is the same. Therefore, no further 
change to this AD is necessary in this regard.

Request To Add Credit for Previous Accomplishment

    One commenter requests that we add a note to the proposed AD, which 
would give credit for work accomplished in compliance with AD 2002-08-
07. The commenter suggests the following note, or language similar to 
this: ``Accomplishment of the actions required by paragraph[s] (a) 
through (l) of AD 2002-08-07 amendment 39-12715, is acceptable for 
compliance

[[Page 5918]]

with the requirements of paragraph[s] (g) through (r) of this AD. This 
AD does not require that those actions be repeated.'' We infer that the 
commenter believes the proposed AD, as written, would require repeating 
work the commenter has already accomplished.
    We do not agree that a credit note is necessary because paragraph 
(e) of this AD, as discussed in the first comment, already gives credit 
for any work previously accomplished. Operators should note that the 
new requirements of paragraph (s) of this AD are applicable only to 
Boeing Model 767-200, -300, and -300F series airplanes, with line 
numbers (L/Ns) 834 through 874 inclusive. Furthermore, if an operator 
previously accomplished these new required actions on any applicable 
airplane (L/Ns 834 through 874 inclusive), then that airplane is also 
in compliance, as stated in paragraph (e) of this AD. Therefore no 
change to this AD is necessary in this regard.

Explanation of Change to This AD

    Boeing has received a Delegation Option Authorization (DOA). We 
have revised this final rule to delegate the authority to approve an 
alternative method of compliance for any repair required by this AD to 
the Authorized Representative for the Boeing DOA Organization rather 
than the Designated Engineering Representative (DER).

Conclusion

    We have carefully reviewed the available data, including the 
comments that have been submitted, and determined that air safety and 
the public interest require adopting the AD with the change described 
previously. We have determined that these changes will neither increase 
the economic burden on any operator nor increase the scope of the AD.

Costs of Compliance

    There are about 848 airplanes of the affected design in the 
worldwide fleet. This AD will affect about 357 airplanes of U.S. 
registry. The new requirements of this AD add no additional economic 
burden for operators affected by AD 2002-08-07. The current costs for 
this AD are repeated for the convenience of affected operators, as 
follows:

                                                                     Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
                                      Work    Average labor
              Action                 hours    rate per hour         Parts           Cost per airplane                       Fleet cost
--------------------------------------------------------------------------------------------------------------------------------------------------------
C.I.C. Application................        1             $65  None...............  $65, per application   $23,205 per application cycle.
                                                                                   cycle.
Cross Bolt Hole Inspection--              2              65  None...............  130..................  46,410.
 Bushings Removed.
Restoration for Bushings Removed..        6              65  None...............  390..................  139,230.
Cross Bolt Inner Chamfer                  2              65  None...............  130, per inspection    46,410, per inspection cycle.
 Inspection--Bushings Not Removed.                                                 cycle.
Restoration for Bushings Not              6              65  None...............  390..................  139,230.
 Removed.
Terminating Action................       64              65  $6,356.............  10,516...............  3,754,212.
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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 this AD:
    (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.
    We prepared a regulatory evaluation of the estimated costs to 
comply with this AD. 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

0
Accordingly, under the authority delegated to me by the Administrator, 
the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

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


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by removing amendment 39-12715 (67 FR 
19322, April 19, 2002), and by adding the following new airworthiness 
directive (AD):

2005-03-03 Boeing: Amendment 39-13959. Docket No. FAA-2004-19201; 
Directorate Identifier 2003-NM-100-AD.

Effective Date

    (a) This AD becomes effective March 11, 2005.

Affected ADs

    (b) This AD supersedes AD 2002-08-07, amendment 39-12715 (67 FR 
19322, April 19, 2002).

Applicability

    (c) This AD applies to all Boeing Model 767-200, -300, and -300F 
series airplanes, certificated in any category.

Unsafe Condition

    (d) This AD was prompted by a report that Titanine JC5A (also 
known as Desoto 823E508) was used on more airplanes during

[[Page 5919]]

production than previously identified. We are issuing this AD to 
prevent severe corrosion in the main landing gear (MLG) outer 
cylinder at the aft trunnion, which could develop into stress 
corrosion cracking and consequent collapse of the MLG.

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.

Requirements of AD 2002-08-07, Amendment 39-12715

Line Numbers (L/N) 1 Through 833 Inclusive, and 875 and Subsequent

    (f) For airplanes with L/Ns 1 through 833 inclusive, and 875 and 
subsequent: Do the actions specified in paragraphs (g) through (q) 
of this AD, as applicable.

Records Examination

    (g) Within 90 days after May 6, 2002 (the effective date of AD 
2002-08-07, amendment 39-12715), examine airplane records to 
determine if Titanine JC5A or Desoto 823E508 (hereafter collectively 
referred to as ``JC5A'') corrosion inhibiting compound (``C.I.C.'') 
was used in the aft trunnion area of the MLG outer cylinder during 
general maintenance, overhaul, or incorporation of Boeing Alert 
Service Bulletin 767-32A0148, dated December 21, 1995, Revision 1, 
dated October 10, 1996 (required by paragraph (e) of AD 96-21-06, 
amendment 39-9783), or Revision 2, dated November 30, 2000; in 
accordance with Boeing Alert Service Bulletin 767-32A0192, dated May 
31, 2001; or Revision 1, dated March 13, 2003. If records do not 
show conclusively which compound was used, assume JC5A was used. 
Refer to Boeing Alert Service Bulletin 767-32A0192, dated May 31, 
2001, for the line numbers of airplanes that were assembled new 
using JC5A.

    Note 1: Prior to January 31, 2001, if BMS 3-27 was ordered from 
Boeing, Boeing shipped JC5A as a substitute.

MLGs on Which JC5A Was Not Used

    (h) Except as provided by paragraph (p) (``Use of JC5A 
Prohibited'') of this AD, if, according to the criteria of paragraph 
(g) of this AD, JC5A was never used, no further action is required 
by this AD.

C.I.C. Applications, Inspections, and Corrective Actions if 
Necessary

    (i) For Category 1 MLG outer cylinders as identified in Boeing 
Alert Service Bulletin 767-32A0192, dated May 31, 2001: If, 
according to the criteria of paragraph (g) of this AD, JC5A may have 
been used, perform the actions specified in both paragraphs (j) and 
(k) of this AD, as applicable, in accordance with Boeing Alert 
Service Bulletin 767-32A0192, dated May 31, 2001; or Revision 1, 
dated March 13, 2003.
    (j) For MLGs and MLG outer cylinders identified in paragraphs 
(j)(1), (j)(2), and (j)(3) of this AD: Within 90 days after May 6, 
2002, perform the C.I.C. application on the MLG in accordance with 
``Part 3--C.I.C. Application'' of the Accomplishment Instructions of 
Boeing Alert Service Bulletin 767-32A0192, dated May 31, 2001; or 
Revision 1, dated March 13, 2003. Thereafter, repeat at intervals 
not to exceed 180 days until the terminating action required by 
paragraph (q) of this AD has been accomplished.
    (1) MLG outer cylinders that are less than 3 years old since 
new.
    (2) MLGs that have been overhauled less than 3 years before May 
6, 2002.
    (3) MLGs on which rework per Boeing Alert Service Bulletin 767-
32A0148, dated December 21, 1995; Revision 1, dated October 10, 
1996; or Revision 2, dated November 30, 2000, was accomplished less 
than 3 years before May 6, 2002.
    (k) Before the MLG outer cylinder is 3 years old since new, 
since last overhaul, or since rework per Boeing Alert Service 
Bulletin 767-32A0148, dated December 21, 1995; Revision 1, dated 
October 10, 1996; or Revision 2, dated November 30, 2000; or within 
90 days after May 6, 2002; whichever is later; perform a detailed 
inspection for cracks and corrosion of the cross bolt bushing holes 
and chamfers in accordance with ``Part 1--Cross Bolt Hole 
Inspection--Bushings Removed'' of the Accomplishment Instructions of 
Boeing Alert Service Bulletin 767-32A0192, dated May 31, 2001; or 
Revision 1, dated March 13, 2003.

    Note 2: For the purposes of this AD, a detailed inspection is 
defined as: ``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.''

    (1) If no crack or corrosion is found during the detailed 
inspection required by paragraph (k) of this AD, perform the actions 
in paragraphs (k)(1)(i), (k)(1)(ii), and (k)(1)(iii) of this AD, at 
the applicable times indicated.
    (i) Before further flight, perform the restoration steps shown 
in Figure 2 of the service bulletin; and thereafter at intervals not 
to exceed 180 days, perform the C.I.C. application on the landing 
gear in accordance with ``Part 3--C.I.C. Application'' of the 
Accomplishment Instructions of the service bulletin.
    (ii) Within 18 months after performing the detailed inspection 
required by paragraph (k) of this AD, and thereafter at intervals 
not to exceed 18 months, perform the detailed inspection for cracks 
and corrosion of the cross bolt hole inner chamfer, in accordance 
with ``Part 2--Cross Bolt Hole Inner Chamfer Inspection--Bushings 
Not Removed'' of the Accomplishment Instructions of the service 
bulletin, until the terminating action required by paragraph (q) of 
this AD has been accomplished.
    (iii) Before the MLG cylinder is 6\1/2\ years old since new, 
since last overhaul, or since rework per Boeing Alert Service 
Bulletin 767-32A0148, dated December 21, 1995; Revision 1, dated 
October 10, 1996; or Revision 2, dated November 30, 2000; whichever 
is later; perform the terminating action described in paragraph (q) 
of this AD.
    (2) If any corrosion is found on the cross bolt holes or outer 
chamfers during the detailed inspection required by paragraph (k) of 
this AD, before further flight, remove the corrosion per Figure 2 of 
the service bulletin.
    (i) If all of the corrosion can be removed: Before further 
flight, perform the restoration steps shown in Figure 2 of the 
service bulletin; thereafter at intervals not to exceed 180 days, 
perform the C.I.C. application on the MLG in accordance with ``Part 
3--C.I.C. Application'' of the Accomplishment Instructions of the 
service bulletin; and perform the terminating action described in 
paragraph (q) of this AD, at the applicable time specified in 
paragraph (k)(2)(i)(A) or (k)(2)(i)(B) of this AD.
    (A) If the MLG outer cylinder is less than 5 years old since 
new, if the MLG was last overhauled less than 5 years before May 6, 
2002, or if rework per Boeing Alert Service Bulletin 767-32A0148, 
dated December 21, 1995; Revision 1, dated October 10, 1996; or 
Revision 2, dated November 30, 2000; was accomplished less than 5 
years before May 6, 2002: Within 18 months after performing the 
detailed inspection required by paragraph (k) of this AD.
    (B) If the MLG outer cylinder is 5 years old or more since new, 
if the MLG was last overhauled 5 years or more before May 6, 2002, 
or if rework per Boeing Alert Service Bulletin 767-32A0148, dated 
December 21, 1995; Revision 1, dated October 10, 1996; or Revision 
2, dated November 30, 2000; was accomplished 5 years or more before 
May 6, 2002: Before the MLG outer cylinder is 6\1/2\ years old since 
new, since last overhaul, or since rework per Boeing Alert Service 
Bulletin 767-32A0148, dated December 21, 1995; Revision 1, dated 
October 10, 1996; or Revision 2, dated November 30, 2000; whichever 
is later.
    (ii) If any corrosion cannot be removed, before further flight, 
perform the terminating action described in paragraph (q) of this 
AD.
    (3) If any crack is found anywhere during the detailed 
inspection required in paragraph (k) of this AD, or if corrosion in 
the inner cross bolt hole chamfers is found, before further flight, 
perform the terminating action described in paragraph (q) of this 
AD.
    (l) For Category 2 MLG outer cylinders as identified in Boeing 
Alert Service Bulletin 767-32A0192, dated May 31, 2001: If, 
according to the criteria of paragraph (g) of this AD, JC5A may have 
been used, perform the actions specified in both paragraphs (m) and 
(n) of this AD, as applicable, in accordance with Boeing Alert 
Service Bulletin 767-32A0192, dated May 31, 2001; or Revision 1, 
dated March 13, 2003.
    (m) For MLGs and MLG outer cylinders identified in paragraphs 
(m)(1) and (m)(2) of this AD: Within 90 days after May 6, 2002, 
perform the C.I.C. application on the MLG in accordance with ``Part 
3--C.I.C. Application'' of the Accomplishment Instructions of Boeing 
Alert Service Bulletin 767-32A0192, dated May 31, 2001; or Revision 
1, dated March 13, 2003. Thereafter, repeat the application at 
intervals not to exceed 180 days until the terminating action 
required by paragraph (q) of this AD has been accomplished.
    (1) MLG outer cylinders that are less than 3 years old since 
new.
    (2) MLGs that have been overhauled less than 3 years before May 
6, 2002.

[[Page 5920]]

    (n) Before the MLG outer cylinder is 3 years old since new or 
since the last overhaul, or within 90 days after May 6, 2002, 
whichever is later, perform a detailed inspection for cracks and 
corrosion of the cross bolt hole inner chamfer, in accordance with 
``Part 2--Cross Bolt Hole Inner Chamfer Inspection--Bushings Not 
Removed'' of the Accomplishment Instructions of Boeing Alert Service 
Bulletin 767-32A0192, dated May 31, 2001; or Revision 1, dated March 
13, 2003.
    (1) If no crack or corrosion is found during the inspection 
required by paragraph (n) of this AD, before further flight, and 
thereafter at intervals not to exceed 180 days, perform the C.I.C. 
application on the MLG in accordance with ``Part 3--C.I.C. 
Application'' of the Accomplishment Instructions of the service 
bulletin, until the next MLG overhaul. After the next MLG overhaul 
has been completed, no further action is required by this AD.
    (2) If any corrosion is found during the detailed inspection 
required by paragraph (n) of this AD, before further flight, remove 
the cross bolt bushings and perform the detailed inspection 
specified in paragraph (k) of this AD, and remove the corrosion per 
Figure 2 of the service bulletin.
    (i) If all of the corrosion can be removed, perform the actions 
specified in paragraph (n)(2)(i)(A) and (n)(2)(i)(B) of this AD, at 
the applicable times indicated.
    (A) Prior to further flight, perform the restoration steps shown 
in Figure 2 of the service bulletin; and thereafter at intervals not 
to exceed 180 days, perform the C.I.C. application on the MLG in 
accordance with ``Part 3--C.I.C. Application'' of the Accomplishment 
Instructions of the service bulletin.
    (B) Within 18 months after the corrosion removal required by 
paragraph (n)(2) of this AD, perform the terminating action 
described in paragraph (q) of this AD.
    (ii) If all the corrosion cannot be removed, before further 
flight, perform the terminating action required by paragraph (q) of 
this AD.
    (3) If any crack is found during the detailed inspection 
required by paragraph (n) of this AD, before further flight, perform 
the terminating action described in paragraph (q) of this AD.

Parts Installation

    (o) As of May 6, 2002, no person shall install on any airplane 
an MLG outer cylinder unless maintenance records conclusively show 
that JC5A has never been used on that MLG outer cylinder, or unless 
it complies with paragraph (q) of this AD.

Use of JC5A Prohibited

    (p) As of May 6, 2002, no person shall use the C.I.C. JC5A in 
the aft trunnion area of the MLG outer cylinder on any airplane.

Terminating Action

    (q) Perform the terminating action (including removal of the 
existing bushings, repair of the aft trunnion area of the outer 
cylinder, and machining and installation of new bushings) in 
accordance with ``Part 4--Terminating Action'' of the Accomplishment 
Instructions of Boeing Alert Service Bulletin 767-32A0192, dated May 
31, 2001; or Revision 1, dated March 13, 2003. Completion of the 
terminating action terminates the requirements for the repetitive 
inspections and C.I.C. applications of this AD.

Credit for Terminating Action

    (r) For all airplanes, accomplishment of the actions specified 
in paragraph (q) of this AD is considered acceptable for compliance 
with the requirements of paragraph (e) of AD 2002-01-13, amendment 
39-12607.

New Requirements of This AD

L/Ns 834 Through 874 Inclusive

    (s) For airplanes with L/Ns 834 through 874 inclusive: Do the 
actions specified in paragraphs (s)(1), (s)(2), and (s)(3) of this 
AD.
    (1) Within 90 days after the effective date of this AD, and 
thereafter at intervals not to exceed 180 days: Do the actions 
specified in paragraph (m) of this AD until the terminating action 
required by paragraph (q) of this AD has been accomplished.
    (2) Before the MLG outer cylinder is 3 years old since new or 
since last overhaul, or within 90 days after the effective date of 
this AD, whichever is later: Do the actions as specified in 
paragraph (n) of this AD.
    (3) As of the effective date of this AD, the actions specified 
in paragraphs (o) and (p) of this AD must be complied with.

Reporting Requirement

    (t) Although the service bulletins referenced in this AD specify 
to submit certain information to the manufacturer, this AD does not 
include such a requirement.

Alternative Methods of Compliance (AMOCs)

    (u)(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) An AMOC that provides an acceptable level of safety may be 
used for any repair required by this AD, if it is approved by an 
Authorized Representative for the Boeing Delegation Option 
Authorization Organization who has been authorized by the Manager, 
Seattle ACO, to make those findings. For a repair method to be 
approved, the repair must meet the certification basis of the 
airplane, and the approval must specifically refer to this AD.

Material Incorporated by Reference

    (v) Unless otherwise specified by this AD, the actions shall be 
done in accordance with Boeing Alert Service Bulletin 767-32A0192, 
dated May 31, 2001; or Boeing Alert Service Bulletin 767-32A0192, 
Revision 1, dated March 13, 2003.
    (1) The Director of the Federal Register approves the 
incorporation by reference of Boeing Alert Service Bulletin 767-
32A0192, Revision 1, dated March 13, 2003 in accordance with 5 
U.S.C. 552(a) and 1 CFR part 51.
    (2) The Director of the Federal Register previously approved the 
incorporation by reference of Boeing Alert Service Bulletin 767-
32A0192, dated May 31, 2001, as of May 6, 2002 (67 FR 19322, April 
19, 2002).
    (3) For copies of the service information, contact Boeing 
Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124-2207. 
For information on the availability of this material at the National 
Archives and Records Administration (NARA), call (202) 741-6030, or 
go to http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html. You may view the AD docket at the 
Docket Management Facility, U.S. Department of Transportation, 400 
Seventh Street SW., room PL-401, Nassif Building, Washington, DC.

    Issued in Renton, Washington, on January 21, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 05-1805 Filed 2-3-05; 8:45 am]
BILLING CODE 4910-13-P