AD 2003-03-02

[Federal Register Volume 68, Number 19 (Wednesday, January 29, 2003)]
[Rules and Regulations]
[Pages 4374-4378]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 03-1827]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2002-NM-308-AD; Amendment 39-13026; AD 2003-03-02]
RIN 2120-AA64


Airworthiness Directives; Boeing Model 767 Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; request for comments.

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SUMMARY: This amendment supersedes an existing airworthiness directive 
(AD), applicable to all Boeing Model 767 series airplanes, that 
currently requires repetitive detailed and eddy current inspections to 
detect cracks of certain midspar fuse pins, and replacement of any 
cracked midspar fuse pin with a new fuse pin. This amendment reduces 
certain compliance times for certain inspections, expands the detailed 
and eddy current inspections, and limits the applicability in the 
existing AD. This amendment also provides for optional terminating 
action, which ends the repetitive inspections. The actions specified in 
this AD are intended to prevent loss of the strut and engine due to 
corrosion damage and cracking of both fuse pins on the same strut. This 
action is intended to address the identified unsafe condition.

DATES: Effective February 13, 2003.
    The incorporation by reference of a certain publication, as listed 
in the regulations, is approved by the Director of the Federal Register 
as of February 13, 2003.
    The incorporation by reference of Boeing Alert Service Bulletin 
767-54A0062, dated April 14, 1994, as listed in the regulations, was 
approved previously by the Director of the Federal Register as of June 
10, 1994 (59 FR 27229, May 26, 1994).
    Comments for inclusion in the Rules Docket must be received on or 
before March 31, 2003.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 2002-NM-308-AD, 1601 Lind Avenue, SW., 
Renton, Washington 98055-4056. Comments may be inspected at this 
location between 9 a.m. and 3 p.m., Monday through Friday, except 
Federal holidays. Comments may be submitted via fax to (425) 227-1232. 
Comments may also be sent via the Internet using the following address: 
<a href="/cdn-cgi/l/email-protection#b1889cd0dfdc9cd8d0c3d2dedcdcd4dfc5f1d7d0d09fd6dec7"><span class="__cf_email__" data-cfemail="063f2b67686b2b6f677465696b6b6368724660676728616970">[email&#160;protected]</span></a>. Comments sent via fax or the Internet must 
contain ``Docket No. 2002-NM-308-AD'' in the subject line and need not 
be submitted in triplicate. Comments sent via the Internet as attached 
electronic files must be formatted in Microsoft Word 97 for Windows or 
ASCII text.
    The service information referenced in this AD may be obtained from 
Boeing Commercial Airplane Group, PO Box 3707, Seattle, Washington 
98124-2207. This information may be examined 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.

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) 
227-2772; fax (425) 227-1181.

[[Page 4375]]


SUPPLEMENTARY INFORMATION: On May 18, 1994, the FAA issued AD 94-11-02, 
amendment 39-8918 (59 FR 27229, June 10, 1994), applicable to all 
Boeing Model 767 series airplanes, to require repetitive detailed 
visual and eddy current inspections to detect cracks of certain midspar 
fuse pins, and replacement of any cracked midspar fuse pin with a new 
fuse pin. That action was prompted by reports of longitudinal fatigue 
cracks on certain midspar fuse pins installed on Boeing Model 767 
series airplanes. The actions required by that AD are intended to 
prevent loss of the strut and engine due to cracking of both fuse pins 
on the same strut.

Actions Since Issuance of Previous Rule

    Since the issuance of AD 94-11-02, an operator has reported a 
fractured outboard midspar fuse pin (part number (P/N) 311T3102-1) of 
the left engine pylon, which was found during a scheduled maintenance 
visit. The fuse pin also had corrosion on the pin and within the bore. 
The airplane had accumulated 9,456 total flight cycles, and 38,911 
total flight hours. The initial inspection for airplanes with midspar 
fuse pins having P/N 311T3102-1, as required by AD 94-11-02, begins 
prior to the accumulation of 15,000 total landings on the fuse pin, or 
within 90 days after the effective date of the existing AD, whichever 
occurs later. In light of this information, the FAA finds it necessary 
to reduce the compliance time for the initial inspection for airplanes 
with midspar fuse pins. This AD also includes inspecting for corrosion 
of the midspar fuse pins, in addition to cracks, and limits the 
applicability in the existing AD.

Explanation of Relevant Service Information

    The FAA has reviewed and approved Boeing Alert Service Bulletin 
767-54A0062, Revision 5, dated November 11, 2002 (Boeing Alert Service 
Bulletin 767-54A0062, dated April 14, 1994, was referenced in the 
existing AD for accomplishment of the actions specified). Revision 5 of 
the service bulletin reduces certain compliance times, references 
certain actions specified in related service bulletins that would 
eliminate the need for the repetitive inspections, and clarifies 
certain procedures. Revision 5 describes procedures for repetitive 
detailed and eddy current inspections for cracks and corrosion of 
certain midspar fuse pins, and replacement of any cracked midspar fuse 
pin with a new fuse pin. The service bulletin also describes procedures 
for a magnetic particle inspection to verify cracks if the fuse pins 
are removed from the strut. Accomplishment of the actions specified in 
the service bulletin is intended to adequately address the identified 
unsafe condition.

Related ADs

    This AD provides an optional terminating action for the repetitive 
inspections by accomplishment of the modification of the nacelle strut 
and wing structure required by the following ADs:
    AD 2000-19-09, amendment 39-11910 (65 FR 58641, October 17, 2000), 
which is applicable to certain Boeing Model 767 series airplanes 
powered by Rolls-Royce RB211 series engines;
    AD 2001-02-07, amendment 39-12091 (66 FR 8085, March 5, 2001), 
which is applicable to certain Boeing Model 767 series airplanes 
powered by Pratt & Whitney engines; and
    AD 2001-06-12, amendment 39-12159 (66 FR 17492, May 7, 2001), which 
is applicable to certain Boeing Model 767 series airplanes powered by 
General Electric engines.
    All the previous ADs require prior or concurrent accomplishment of 
the following service bulletins, which are specified in Service 
Bulletin 767-54A0062, Revision 5, as the appropriate sources of service 
information for accomplishment of the rework of the side load fitting 
and tension fasteners, as applicable, and replacement of midspar fuse 
pins or modification of the nacelle strut and wing structure. Doing 
either of these actions would eliminate the need for the repetitive 
inspections specified in Service Bulletin 767-54A0062, Revision 5.
    [sbull] Boeing Service Bulletin 767-54-0069, Revision 1, dated 
January 29, 1998, describes procedures for rework of the side load 
fitting and tension fasteners, as applicable, and replacement of 
midspar fuse pins with new, higher-strength midspar fuse pins. The 
rework involves increasing the size of the tension bolts of the inboard 
and outboard side load fittings. The replacement also involves 
installing new, higher-strength bolts and radius fillers in the side 
load fittings and backup support structure, and installing higher-
strength fasteners common to the front spar and rib number 8 rib post.
    [sbull] Boeing Service Bulletin 767-54-0080, dated October 7, 1999, 
describes procedures for modification of the nacelle strut and wing 
structure. The modification consists of replacing many of the 
significant load-bearing components of the strut (e.g., the side link 
fittings assemblies, the midspar fittings, the side load fittings, 
certain fuse bolt assemblies) with improved components.
    [sbull] Boeing Service Bulletin 767-54-0081, dated July 29, 1999, 
describes procedures for modification of the nacelle strut and wing 
structure. The modification consists of replacing many of the 
significant load-bearing components of the strut and wing (e.g., the 
side link fittings, the midspar fittings, the side load fittings, 
certain fuse pin assemblies) with improved components.
    [sbull] Boeing Service Bulletin 767-54-0082, dated October 28, 
1999, describes procedures for modification of the nacelle strut and 
wing structure. The modification consists of replacing many of the 
significant load-bearing components of the strut-to-wing attachment 
(e.g., midspar fuse pins, side links, side link fuse pins, diagonal 
brace, and diagonal brace fuse pins) with improved components.

Explanation of Requirements of Rule

    Since an unsafe condition has been identified that is likely to 
exist or develop on other airplanes of this same type design, this AD 
supersedes AD 94-11-02 to continue to require repetitive detailed and 
eddy current inspections to detect cracks of certain midspar fuse pins, 
and replacement of any cracked midspar fuse pin with a new fuse pin. 
This AD reduces certain compliance times for certain inspections, 
expands certain detailed and eddy current inspections, and limits the 
applicability in the existing AD.

Difference Between This AD and Service Bulletin

    Boeing Alert Service Bulletin 767-54A0062, Revision 5, specifies 
that all actions for which the Boeing 767 Airplane Maintenance Manual 
(AMM) is specified as the appropriate source of service information for 
work instructions may instead be done according to an ``operator's 
equivalent procedure.'' However, this AD requires that engine removal 
and support, when any fuse pin is removed from a strut, must be 
accomplished per the procedures specified the applicable section of the 
AMM. An ``operator's equivalent procedure'' may be used only if 
approved as an alternative method of compliance per paragraph (o)(1) of 
this AD.

Explanation of Change Made to Existing Requirements

    The FAA has changed all references to a ``detailed visual 
inspection'' in the existing AD to ``detailed inspection'' in this AD. 
Additionally, a note has been

[[Page 4376]]

added to this AD to define that inspection.

Determination of Rule's Effective Date

    Since a situation exists that requires the immediate adoption of 
this regulation, it is found that notice and opportunity for prior 
public comment hereon are impracticable, and that good cause exists for 
making this amendment effective in less than 30 days.

Comments Invited

    Although this action is in the form of a final rule that involves 
requirements affecting flight safety and, thus, was not preceded by 
notice and an opportunity for public comment, comments are invited on 
this rule. Interested persons are invited to comment on this rule by 
submitting such written data, views, or arguments as they may desire. 
Communications shall identify the Rules Docket number and be submitted 
in triplicate to the address specified under the caption ADDRESSES. All 
communications received on or before the closing date for comments will 
be considered, and this rule may be amended in light of the comments 
received. Factual information that supports the commenter's ideas and 
suggestions is extremely helpful in evaluating the effectiveness of the 
AD action and determining whether additional rulemaking action would be 
needed.
    Submit comments using the following format:
    [sbull] Organize comments issue-by-issue. For example, discuss a 
request to change the compliance time and a request to change the 
service bulletin reference as two separate issues.
    [sbull] For each issue, state what specific change to the AD is 
being requested.
    [sbull] Include justification (e.g., reasons or data) for each 
request.
    Comments are specifically invited on the overall regulatory, 
economic, environmental, and energy aspects of the rule that might 
suggest a need to modify the rule. All comments submitted will be 
available, both before and after the closing date for comments, in the 
Rules Docket for examination by interested persons. A report that 
summarizes each FAA-public contact concerned with the substance of this 
AD will be filed in the Rules Docket.
    Commenters wishing the FAA to acknowledge receipt of their comments 
submitted in response to this rule must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket Number 2002-NM-308-AD.'' The postcard will be date stamped 
and returned to the commenter.

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.
    The FAA has determined that this regulation is an emergency 
regulation that must be issued immediately to correct an unsafe 
condition in aircraft, and that it is not a ``significant regulatory 
action'' under Executive Order 12866. It has been determined further 
that this action involves an emergency regulation under DOT Regulatory 
Policies and Procedures (44 FR 11034, February 26, 1979). If it is 
determined that this emergency regulation otherwise would be 
significant under DOT Regulatory Policies and Procedures, a final 
regulatory evaluation will be prepared and placed in the Rules Docket. 
A copy of it, if filed, 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.

Sec.  39.13  [Amended]

    2. Section 39.13 is amended by removing amendment 39-8918 (59 FR 
27229, June 10, 1994), and by adding a new airworthiness directive 
(AD), amendment 39-13026, to read as follows:

2003-03-02 Boeing: Amendment 39-13026. Docket 2002-NM-308-AD. 
Supersedes AD 94-11-02, Amendment 39-8918.

    Applicability: Model 767-200, -300, and -300F series airplanes, 
as listed in Boeing Alert Service Bulletin 767-54A0062, Revision 5, 
dated November 11, 2002; 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 (o)(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 loss of the strut and engine due to corrosion damage 
and cracking of both fuse pins on the same strut, accomplish the 
following:

Restatement of Requirements of AD 94-11-02

Repetitive Inspections

    (a) For airplanes having midspar fuse pins, part number (P/N) 
311T3102-1: Perform a detailed inspection and an eddy current 
inspection to detect cracks of the midspar fuse pins, in accordance 
with Boeing Alert Service Bulletin 767-54A0062, dated April 14, 
1994; or Boeing Alert Service Bulletin 767-54A0062, Revision 5, 
dated November 11, 2002; at the time specified in paragraph (a)(1), 
(a)(2), (a)(3), or (a)(4) of this AD, as applicable. Repeat these 
inspections thereafter at intervals not to exceed 3,000 landings 
until accomplishment of the initial inspections specified in 
paragraph (h) of this AD.

    Note 2: For the purposes of this AD, a detailed inspection is 
defined as: ``An intensive visual examination of a specific 
structural area, system, installation, or assembly to detect damage, 
failure, or irregularity. Available lighting is normally 
supplemented with a direct source of good lighting at intensity 
deemed appropriate by the inspector. Inspection aids such as mirror, 
magnifying lenses, etc., may be used. Surface cleaning and elaborate 
access procedures may be required.''

    (1) For airplanes having midspar fuse pins that have accumulated 
18,000 or more total landings as of June 10, 1994 (the effective 
date of AD 94-11-02, amendment 39-8918), accomplish the inspections 
within 60 days after June 10, 1994.
    (2) For airplanes having midspar fuse pins that have accumulated 
15,000 or more total landings, but less than 18,000 total landings, 
as of June 10, 1994, accomplish the inspections within 90 days after 
June 10, 1994.

[[Page 4377]]

    (3) For airplanes having midspar fuse pins that have accumulated 
10,000 or more total landings, but less than 15,000 total landings, 
as of June 10, 1994, accomplish the inspections within 120 days 
after June 10, 1994.
    (4) For airplanes having midspar fuse pins that have accumulated 
less than 10,000 total landings as of June 10, 1994, accomplish the 
inspections prior to the accumulation of 10,000 total landings on 
the fuse pin, or within 120 days after June 10, 1994, whichever 
occurs later.
    (b) For airplanes having a midspar fuse pin, P/N 311T3102-2 or 
311T2102-1: Prior to the accumulation of 15,000 total landings on 
the fuse pin, or within 90 days after June 10, 1994, whichever 
occurs later, perform a detailed inspection and an eddy current 
inspection to detect cracks on the midspar fuse pins, in accordance 
with Boeing Alert Service Bulletin 767-54A0062, dated April 14, 
1994; or Boeing Alert Service Bulletin 767-54A0062, Revision 5, 
dated November 11, 2002. Repeat these inspections thereafter at 
intervals not to exceed 3,000 landings until accomplishment of 
paragraph (h) of this AD.

Replacement/Repetitive Inspections

    (c) If any crack is found during an inspection required by 
paragraph (a) or (b) of this AD, prior to further flight, replace 
the cracked midspar fuse pin with a new fuse pin, in accordance with 
Boeing Alert Service Bulletin 767-54A0062, dated April 14, 1994; or 
Boeing Alert Service Bulletin 767-54A0062, Revision 5, dated 
November 11, 2002. Thereafter, perform the detailed and eddy current 
inspections specified in paragraph (a) or (b) of this AD, as 
applicable, on the new fuse pin at the time specified in paragraph 
(c)(1) or (c)(2) of this AD.
    (1) For airplanes having midspar fuse pins, P/N 311T3102-1: 
Perform the initial inspection of the new fuse pin prior to the 
accumulation of 10,000 total landings on the new fuse pin. Repeat 
the inspection thereafter at intervals not to exceed 3,000 landings 
until accomplishment of paragraph (j) of this AD.
    (2) For airplanes having midspar fuse pins, P/Ns 311T3102-2 and 
311T2102-1: Perform the initial inspection of the new fuse pin prior 
to the accumulation of 15,000 total landings on the new fuse pin. 
Repeat the inspection thereafter at intervals not to exceed 3,000 
landings until accomplishment of paragraph (j) of this AD.

Fuse Pin Removal

    (d) When any fuse pin is removed from a strut equipped with a 
General Electric engine, the engine must be removed in accordance 
with procedures described in the Boeing 767 Maintenance Manual, 
subject 71-00-02; or supported in accordance with a method approved 
by the Manager, Seattle Aircraft Certification Office (ACO), FAA, 
Transport Airplane Directorate.
    (e) When any fuse pin is removed from a strut equipped with a 
Pratt & Whitney engine, the engine must be removed in accordance 
with procedures described in the Boeing 767 Maintenance Manual, 
subject 71-00-02; or supported in accordance with procedures 
described in the Boeing 767 Maintenance Manual, subject 54-51-02, 
Temporary Revisions (TR), dated April 22, 1994; or supported in 
accordance with a method approved by the Manager, Seattle ACO.
    (f) When any fuse pin is removed from a strut equipped with a 
Rolls-Royce engine, the engine must be removed in accordance with 
procedures described in the Boeing 767 Maintenance Manual, subject 
71-00-02; or supported in accordance with procedures described in 
the Boeing 767 Maintenance Manual, subject 54-51-02; or supported in 
accordance with a method approved by the Manager, Seattle ACO.
    (g) Any midspar fuse pin, P/N 311T3102-1, 311T3102-2, or 
311T2102-1, that has been removed from the strut and inspected for 
cracks using the 100 percent magnetic particle inspection technique 
described in Boeing Alert Service Bulletin 767-54A0062, dated April 
14, 1994; or Boeing Alert Service Bulletin 767-54A0062, Revision 5, 
dated November 11, 2002; may be reinstalled on the strut provided 
that the fuse pin is found to be crack-free during the magnetic 
particle inspection. Prior to the accumulation of 3,000 total 
landings after reinstallation of the fuse pin, the fuse pin must be 
inspected in accordance with the requirements of paragraph (a), (b), 
or (h) of this AD, as applicable.

New Requirements of this AD

Initial and Repetitive Inspections

    (h) For airplanes having midspar fuse pins, P/Ns 311T3102-1, 
311T3102-2, 311T3102-3, 311T3102-4, 311T2102-1 or 311T2102-2: Do a 
detailed inspection and an eddy current inspection for cracks and 
corrosion per Boeing Alert Service Bulletin 767-54A0062, Revision 5, 
dated November 11, 2002. Do the inspections at the later of the 
times specified in paragraphs (h)(1) and (h)(2) of this AD. Repeat 
the inspections at least every 3,000 landings or 5 years, whichever 
is first. Accomplishment of the initial inspections in this 
paragraph ends the repetitive inspections required by paragraphs (a) 
and (b) of this AD.
    (1) Before the accumulation of 5,000 total landings on the fuse 
pin or within 5 years after fuse pin installation, whichever is 
first.
    (2) Within 30 days after the effective date of this AD.

Corrective Action

    (i) If any crack or corrosion is found during any inspection 
required by paragraph (h) of this AD, before further flight, do the 
actions required by paragraph (i)(1) or (i)(2) of this AD, as 
applicable, per Boeing Alert Service Bulletin 767-54A0062, Revision 
5, dated November 11, 2002.
    (1) If any crack is found, replace the midspar fuse pin with a 
new fuse pin.
    (2) If any corrosion is found, repair the midspar fuse pin or 
replace with a new fuse pin.

Repetitive Inspections

    (j) For airplanes identified in paragraph (h) of this AD: After 
the installation of a new midspar fuse pin, inspect the new fuse pin 
per paragraph (h) of this AD before the accumulation of 5,000 total 
landings on the fuse pin or within 5 years, whichever is first. 
Repeat the inspections at least every 3,000 landings or 5 years, 
whichever is first Accomplishment of this paragraph ends the 
repetitive inspections required by paragraph (c) of this AD.

Optional Terminating Action

    (k) For all airplanes: Accomplishment of the rework of the side 
load fitting and tension fasteners, as applicable, and replacement 
of midspar fuse pins per Boeing Service Bulletin 767-54-0069, dated 
October 9, 1997; Revision 1, dated January 29, 1998; or Revision 2, 
dated August 31, 2000; ends the repetitive inspections required by 
this AD.
    (l) Modification of the nacelle strut and wing structure as 
required by AD 2000-19-09, amendment 39-11910 (applicable to certain 
Boeing Model 767 series airplanes powered by Rolls-Royce RB211 
series engines); AD 2001-02-07, amendment 39-12091 (applicable to 
certain Boeing Model 767 series airplanes powered by Pratt & Whitney 
engines); or AD 2001-06-12, amendment 39-12159 (applicable to 
certain Boeing Model 767 series airplanes powered by General 
Electric engines); as applicable; ends the repetitive inspections 
required by this AD.

[[Page 4378]]

``Operator's Equivalent Procedure''

    (m) Though Boeing Alert Service Bulletin 767-54A0062, Revision 
5, dated November 11, 2002, specifies that an ``operator's 
equivalent procedure'' may be used for all actions for which the 
Boeing 767 Airplane Maintenance Manual (AMM) is specified as the 
appropriate source of service information: Engine removal and 
support, when any fuse pin is removed from a strut, must be done 
according to the applicable section of the Boeing 767 Airplane 
Maintenance Manual, as specified in the service bulletin.

Actions Done per Previously Issued Service Information

    (n) Inspections and replacements done before the effective date 
of this AD per Boeing Alert Service Bulletin 767-54A0062, Revision 
1, dated May 11, 1994; Revision 2, dated December 21, 1994; Revision 
3, dated June 15, 1995; or Revision 4, dated May 7, 1998; are 
acceptable for compliance with the applicable actions specified in 
this AD.

Alternative Methods of Compliance

    (o)(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 ACO. 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 94-11-02, amendment 39-8918, are approved as 
alternative methods of compliance with the applicable actions 
specified in this AD.

    Note 3: 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

    (p) 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

    (q) Unless otherwise provided in this AD, the actions shall be 
done in accordance with Boeing Alert Service Bulletin 767-54A0062, 
dated April 14, 1994; and Boeing Alert Service Bulletin 767-54A0062, 
Revision 5, dated November 11, 2002.
    (1) The incorporation by reference of Boeing Alert Service 
Bulletin 767-54A0062, Revision 5, dated November 11, 2002, is 
approved by the Director of the Federal Register in accordance with 
5 U.S.C. 552(a) and 1 CFR part 51.
    (2) The incorporation by reference of Boeing Alert Service 
Bulletin 767-54A0062, dated April 14, 1994, was approved previously 
by the Director of the Federal Register as of June 10, 1994 (59 FR 
27229, May 26, 1994).
    (3) Copies may be obtained from Boeing Commercial Airplane 
Group, PO 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 Office of the Federal 
Register, 800 North Capitol Street, NW., suite 700, Washington, DC.

Effective Date

    (r) This amendment becomes effective on February 13, 2003.

    Issued in Renton, Washington, on January 22, 2003.
Vi L. Lipski,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 03-1827 Filed 1-28-03; 8:45 am]
BILLING CODE 4910-13-P