[Federal Register Volume 67, Number 78 (Tuesday, April 23, 2002)]
[Rules and Regulations]
[Pages 19661-19663]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 02-9613]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-NM-209-AD; Amendment 39-12723; AD 2002-08-15]
RIN 2120-AA64


Airworthiness Directives; Boeing Model 767 Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment adopts a new airworthiness directive (AD), 
applicable to certain Boeing Model 767 series airplanes, that requires 
an inspection of the tripod strut assembly of the inboard support of 
the leading edge slat of the wing for a preload condition, and follow-
on actions. For certain airplanes, this AD also requires inspection and 
replacement of the existing tripod struts with new, adjustable struts, 
if necessary. This action is necessary to prevent damage to the tripod 
strut assembly due to a preload condition, which could result in loss 
of control of the inboard leading edge slat or separation of the slat 
from the airplane, and consequent reduced controllability of the 
airplane. This action is intended to address the identified unsafe 
condition.

DATES: Effective May 28, 2002.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of May 28, 2002.

ADDRESSES: The service information referenced in this AD may be 
obtained from Boeing Commercial Airplane Group, 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 Office of 
the Federal Register, 800 North Capitol Street, NW., suite 700, 
Washington, DC.

[[Page 19662]]


FOR FURTHER INFORMATION CONTACT: John Craycraft, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
227-2782; fax (425) 227-1181.

SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) to include an airworthiness 
directive (AD) that is applicable to certain Boeing Model 767 series 
airplanes was published in the Federal Register on January 2, 2002 (67 
FR 35). That action proposed to require an inspection of the tripod 
strut assembly of the inboard support of the leading edge slat of the 
wing for a preload condition, and follow-on actions. For certain 
airplanes, that action also proposed to require inspection and 
replacement of the existing tripod struts with new, adjustable struts, 
if necessary.

Comments

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. No comments were submitted in response 
to the proposal or the FAA's determination of the cost to the public.

Conclusion

    The FAA has determined that air safety and the public interest 
require the adoption of the rule as proposed.

Cost Impact

    There are approximately 379 Model 767 series airplanes of the 
affected design in the worldwide fleet. The FAA estimates that 136 
airplanes of U.S. registry will be affected by this AD.
    It will take approximately 1 work hour per airplane to accomplish 
the required inspections of the tripod strut assembly and bushing 
holes, at an average labor rate of $60 per work hour. Based on these 
figures, the cost impact of the inspections required by this AD on U.S. 
operators is estimated to be $8,160, or $60 per airplane.
    The cost impact figure discussed above is based on assumptions that 
no operator has yet accomplished any of the requirements of this AD 
action, and that no operator would accomplish those actions in the 
future if this AD were not adopted. The cost impact figures discussed 
in AD rulemaking actions represent only the time necessary to perform 
the specific actions actually required by the AD. These figures 
typically do not include incidental costs, such as the time required to 
gain access and close up, planning time, or time necessitated by other 
administrative actions.
    Should an operator be required to accomplish the rework of the 
fitting assembly, it will take approximately 4 work hours per airplane, 
at an average labor rate of $60 per work hour. Based on these figures, 
the cost impact of this rework, if accomplished, will be $240 per 
airplane.
    Should an operator be required to accomplish the high frequency 
eddy current inspection, it will take approximately 5 work hours per 
airplane, at an average labor rate of $60 per work hour. Based on these 
figures, the cost impact of this inspection, if accomplished, will be 
$300 per airplane.
    Should an operator be required to accomplish the replacement of the 
main strut support fitting, it will take approximately 14 work hours 
per airplane to accomplish the replacement (on both the left and right 
wings of the airplane, excluding the time for gaining access and 
closing up), at an average labor rate of $60 per work hour. Required 
parts will cost approximately $12,380 per airplane. Based on these 
figures, the cost impact of the replacement, if accomplished, will be 
$13,220 per airplane.
    Should an operator be required to accomplish the inspection for 
improperly cut and spliced struts, it will take approximately 1 work 
hour per airplane, at an average labor rate of $60 per work hour. Based 
on these figures, the cost impact of this inspection, if accomplished, 
will be $60 per airplane.
    Should an operator be required to accomplish the replacement of a 
cut and spliced strut with a new, adjustable tripod strut, it will take 
approximately 4 work hours per airplane, at an average labor rate of 
$60 per work hour. Based on these figures, the cost impact of this 
replacement, if accomplished, will be $240 per airplane.

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.


Sec. 39.13  [Amended]

    2. Section 39.13 is amended by adding the following new 
airworthiness directive:

2002-08-15  Boeing: Amendment 39-12723. Docket 2001-NM-209-AD.

    Applicability: Model 767 series airplanes, line numbers 160 
through 541 inclusive, 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 (e) 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 damage to the tripod strut assembly due to a preload 
condition, which could result in loss of control of the inboard 
leading edge slat or separation of the slat from the airplane, and 
consequent reduced controllability of the airplane, accomplish the 
following:

Inspections

    (a) For all airplanes: Before the accumulation of 5,000 total 
flight cycles or within 24 months after the effective date of this 
AD, whichever is later: Do a general visual inspection (check) of 
the tripod strut assembly of the inboard leading edge slat of

[[Page 19663]]

each wing for a preload condition, per Figure 2 of Boeing Service 
Bulletin 767-57A0058, Revision 1, dated May 27, 1999.

    Note 2: For the purposes of this AD, a general visual inspection 
is defined as: ``A visual examination of an interior or exterior 
area, installation, or assembly to detect obvious damage, failure, 
or irregularity. This level of inspection is made under normally 
available lighting conditions such as daylight, hangar lighting, 
flashlight, or drop-light and may require removal or opening of 
access panels or doors. Stands, ladders, or platforms may be 
required to gain proximity to the area being checked.''

    (1) If no preload condition is found, before further flight, 
inspect the fitting assembly bushing holes for roundness, per Figure 
5 of the Accomplishment Instructions of the service bulletin.
    (i) If all the bushing holes are round, before further flight, 
do the inspection required by paragraph (c) of this AD.
    (ii) If any bushing hole is not round, before further flight, do 
the inspections required by paragraphs (b) and (c) of this AD.
    (2) If a preload condition is found, before further flight, do 
the inspections required by paragraphs (b) and (c) of this AD.

Follow-on Actions

    (b) For airplanes subject to paragraph (a)(1)(ii) or (a)(2) of 
this AD: Do a high frequency eddy current inspection of the fitting 
assembly lug for cracking, per Figure 6 of the Accomplishment 
Instructions of Boeing Service Bulletin 767-57A0058, Revision 1, 
dated May 27, 1999.
    (1) If no cracking is found, or if cracking is found in the lug 
bore only, before further flight, rework the fitting assembly lug, 
per Figure 7 of the Accomplishment Instructions of the service 
bulletin.
    (2) If cracking is found in the fitting lug base or the lug bore 
and base, before further flight, purge the auxiliary fuel tank and 
replace the fitting assembly lug, per Figure 8 of the Accomplishment 
Instructions of the service bulletin.
    (c) For airplanes subject to paragraph (a)(1)(i), (a)(1)(ii), or 
(a)(2) of this AD: Do a general visual inspection of the bushing 
holes of the main strut assembly to determine if the bushing holes 
are round, per Figure 9 of the Accomplishment Instructions of Boeing 
Service Bulletin 767-57A0058, Revision 1, dated May 27, 1999.
    (1) If the bushing holes are round, before further flight, 
assemble the tripod assembly, per Figure 11 or Figure 12, as 
applicable, of the Accomplishment Instructions of the service 
bulletin.
    (2) If the bushing holes are not round, before further flight, 
replace the main strut fitting assembly, per Figure 10 of the 
Accomplishment Instructions of the service bulletin; then assemble 
the tripod assembly, per Figure 11 or Figure 12, as applicable, of 
the Accomplishment Instructions of the service bulletin.

    Note 3: Inspections and follow-on actions done before the 
effective date of this AD per Boeing Alert Service Bulletin 767-
57A0058, dated June 11, 1998, are considered acceptable for 
compliance with the applicable actions specified in this AD.

Inspection/Replacement of Tripod Struts

    (d) For Group 2 airplanes that have not accomplished Boeing 
Service Bulletin 767-57-0037, dated January 14, 1993: Before further 
flight after doing the inspections and follow-on actions required by 
paragraphs (a), (b), and (c) of this AD, do a general visual 
inspection of the tripod struts to determine if they have been cut 
and spliced, per the Accomplishment Instructions of the service 
bulletin.
    (1) If the tripod struts have been cut and spliced with fewer 
than six hi-loks, before further flight, replace with new, 
adjustable struts, per Figure 1 of the Accomplishment Instructions 
of the service bulletin.
    (2) If the tripod struts have not been cut and spliced, or they 
have been cut and spliced with six hi-loks, no further action is 
required by this paragraph.

Alternative Methods of Compliance

    (e) An alternative method of compliance or adjustment of the 
compliance time that provides an acceptable level of safety may be 
used if approved by the Manager, Seattle Aircraft Certification 
Office (ACO), FAA. Operators shall submit their requests through an 
appropriate FAA Principal Maintenance Inspector, who may add 
comments and then send it to the Manager, Seattle ACO.

    Note 4: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Seattle ACO.

Special Flight Permits

    (f) 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

    (g) The actions shall be done in accordance with Boeing Service 
Bulletin 767-57A0058, Revision 1, dated May 27, 1999; and Boeing 
Service Bulletin 767-57-0037, dated January 14, 1993; as applicable. 
This incorporation by reference was approved by the Director of the 
Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 
51. Copies may be obtained from Boeing Commercial Airplane Group, 
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 Office of the Federal 
Register, 800 North Capitol Street, NW., suite 700, Washington, DC.

Effective Date

    (h) This amendment becomes effective on May 28, 2002.


    Issued in Renton, Washington, on April 15, 2002.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 02-9613 Filed 4-22-02; 8:45 am]
BILLING CODE 4910-13-U