[Federal Register Volume 64, Number 243 (Monday, December 20, 1999)]
[Rules and Regulations]
[Pages 71006-71007]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-32507]



[[Page 71006]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97-NM-186-AD; Amendment 39-11468; AD 99-26-09]
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 
repetitive inspections to ensure the proper condition of the engine 
thrust link components, and follow-on corrective action, if necessary; 
and replacement of the end cap assembly with an improved assembly. Such 
replacement, when accomplished, terminates the repetitive inspections. 
This amendment is prompted by a report of fatigue cracking of end cap 
bolts caused by improper installation. The actions specified by this AD 
are intended to prevent failure of the end cap assembly, which could 
lead to separation of the engine from the airplane in the event of a 
primary thrust linkage failure.

DATES: Effective January 24, 2000.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of January 24, 2000.

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.

FOR FURTHER INFORMATION CONTACT: James G. Rehrl, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA, Transport Airplane Directorate, Seattle 
Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, 
Washington 98055-4056; telephone (425) 227-2783; 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 as a supplemental notice of proposed rulemaking 
(NPRM) in the Federal Register on October 21, 1999 (64 FR 56709). That 
action proposed to require repetitive inspections to ensure the proper 
condition of the engine thrust link components, and follow-on 
corrective action, if necessary; and replacement of the end cap 
assembly with an improved assembly. Such replacement, when 
accomplished, terminates the repetitive inspections. That action also 
revises the proposed rule by adding a repair requirement and by 
clarifying the type of inspection and terminology used in describing 
the parts to be inspected.

Comments

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due consideration has been given to 
the single comment received.
    The Air Transport Association of America (ATA), on behalf of its 
members, supports the proposed rule. The ATA states that responding 
members indicated that they had no comment or no objection to the 
proposed rule.

Conclusion

    After careful review of the available data, including the comment 
noted above, the FAA has determined that air safety and the public 
interest require the adoption of the rule as proposed.

Cost Impact

    There are approximately 239 Model 767 series airplanes of the 
affected design in the worldwide fleet. The FAA estimates that 96 
airplanes of U.S. registry will be affected by this AD, that it will 
take approximately 37 work hours per airplane (18.5 work hours per 
engine) to accomplish the required inspections, and that the average 
labor rate is $60 per work hour. Based on these figures, the cost 
impact of this AD on U.S. operators is estimated to be $213,120, or 
$2,220 per airplane, per inspection cycle.
    It will take approximately 135 work hours per airplane (67.5 work 
hours per engine) to accomplish the required replacement of the forward 
engine mount end cap and bolts, at an average labor rate of $60 per 
work hour. Required parts will cost approximately $1,000 per airplane. 
Based on these figures, the cost impact of the AD on U.S. operators is 
estimated to be $873,600, or $9,100 per airplane.
    The cost impact figures discussed above are based on assumptions 
that no operator has yet accomplished any of the requirements of this 
AD action, and that no operator would accomplish those actions in the 
future if this AD were not adopted.

Regulatory Impact

    The regulations adopted herein will not have substantial direct 
effects 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, in 
accordance with Executive Order 12612, it is determined that this final 
rule does not have sufficient federalism implications to warrant the 
preparation of a Federalism Assessment.
    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:

99-26-09 Boeing: Amendment 39-11468. Docket 97-NM-186-AD.

    Applicability: Model 767 series airplanes, powered by Pratt & 
Whitney Model JT9D or Model PW4000 series engines, as listed in 
Boeing Alert Service Bulletin 767-71A0087, dated October 10, 1996; 
certificated in any category.

    Note 1: This AD applies to each airplane identified in the 
preceding applicability provision, regardless of whether it has been

[[Page 71007]]

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 possible separation of the engine from the airplane 
in the event of a primary thrust linkage failure, accomplish the 
following:

Initial and Repetitive Inspections

    (a) For Groups 1 and 2 airplanes: Accomplish paragraphs (a)(1), 
(a)(2), and (a)(3) of this AD, as applicable, in accordance with 
Boeing Alert Service Bulletin 767-71A0087, dated October 10, 1996.
    (1) Within 500 flight hours or 300 flight cycles after the 
effective date of this AD, whichever occurs later: Accomplish Work 
Package 1 (a detailed visual inspection of the forward engine mount 
to ensure that the thrust link, evener bar, associated lugs, and 
attaching hardware are firmly attached). Thereafter, repeat Work 
Package 1 at the intervals specified in the alert service bulletin 
until the requirements of either paragraph (a)(2) or (a)(3) of this 
AD are accomplished.

    Note 2: For the purposes of this AD, a detailed visual 
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 an 
intensity deemed appropriate by the inspector. Inspection aids such 
as mirrors, magnifying lenses, etc. may be used. Surface cleaning 
and elaborate access procedures may be required.''

    (2) Prior to the accumulation of 16,000 total flight cycles on 
any engine or within 500 flight hours or 300 flight cycles after the 
effective date of this AD, whichever occurs later: Accomplish Work 
Package 2 (non-destructive test inspection of the forward engine 
mount to ensure the proper condition of the engine thrust link 
components). Thereafter, repeat Work Package 2 on that engine at the 
intervals specified in the alert service bulletin until the 
requirements of paragraph (a)(3) of this AD are accomplished. 
Accomplishment of Work Package 2 constitutes terminating action for 
the repetitive inspections required by paragraph (a)(1) of this AD 
for that engine.

Replacement and Terminating Action

    (3) Within 3 years after the effective date of this AD: 
Accomplish Work Package 3 (end cap and bolt replacement of the 
forward engine mount). Accomplishment of Work Package 3 constitutes 
terminating action for the requirements of this AD for Groups 1 and 
2 airplanes.
    (b) For Group 3 airplanes: Within 3 years after the effective 
date of this AD, accomplish Work Package 4 (bolt replacement) in 
accordance with Boeing Alert Service Bulletin 767-71A0087, dated 
October 10, 1996.

Repair and Replacement Action

    (c) For all airplanes: If any discrepancy (including an 
improperly installed or damaged engine thrust link component) is 
found during any inspection required by this AD, prior to further 
flight, accomplish the actions required by paragraphs (c)(1) and 
(c)(2) of this AD.
    (1) Repair any discrepancies in accordance with a method 
approved by the Manager, Seattle Aircraft Certification Office 
(ACO), FAA, Transport Airplane Directorate. 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.
    (2) Accomplish Work Package 3 in accordance with Boeing Alert 
Service Bulletin 767-71A0087, dated October 10, 1996.

Spares

    (d) As of the effective date of this AD, no person shall install 
a forward engine mount end cap having part number 310T3026-1 on any 
airplane.

Alternative Method 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 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.

    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

    (f) Special flight permits may be issued in accordance with 
Secs. 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) Except as provided by paragraph (c)(1) of this AD, the 
actions shall be done in accordance with Boeing Alert Service 
Bulletin 767-71A0087, dated October 10, 1996. 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.
    (h) This amendment becomes effective on January 24, 2000.

    Issued in Renton, Washington, on December 9, 1999.
D.L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 99-32507 Filed 12-17-99; 8:45 am]
BILLING CODE 4910-13-P