[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
