[Federal Register Volume 61, Number 132 (Tuesday, July 9, 1996)]
[Rules and Regulations]
[Pages 35938-35940]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 96-16950]
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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39
[Docket No. 95-NM-124-AD; Amendment 39-9687; AD 96-14-05]
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 supersedes an existing airworthiness directive
(AD), applicable to certain Boeing Model 767 series airplanes, that
currently requires an inspection of the control rods of the outboard
leading edge slat, and follow-on actions (including repetitive
ultrasonic inspections), if necessary. For certain airplanes, that AD
also requires replacement of the control rod ends and attach bolts. It
also provides for an optional terminating action for follow-on
repetitive inspections. That AD was prompted by reports of cracks and
worn attach bolts of the control rods of the leading edge outboards
slats of the wings due to the high breakout torque in the joint of the
control rod end. This amendment requires the installation of the
previously optional terminating action. The actions specified by this
AD are intended to prevent reduced controllability of the airplane and
damage in the slat structure or fixed leading edge of the wing, as a
result of cracks and worn attach bolts.
DATES: Effective August 13, 1996.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of August 13, 1996.
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: Kristin Larson, Aerospace Engineer,
Systems and Equipment Branch, ANM-130S, FAA, Seattle Aircraft
Certification Office, 1601 Lind Avenue, SW., Renton, Washington;
telephone (206) 227-1760; fax (206) 227-1181.
SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal
Aviation Regulations (14 CFR part 39) by superseding AD 90-20-16,
amendment 39-6726 (55 FR 37858, September 14, 1990), which is
applicable to certain Boeing Model 767 series airplanes, was published
in the Federal Register on December 13, 1995 (60 FR 63990). The action
proposed to continue to require a one-time visual inspection to
determine the date of manufacture of the control rods of the outboard
leading edge slat, and follow-on actions (i.e., repetitive ultrasonic
inspection), if necessary. The action also proposed to continue to
require replacement of the control rod ends and attach bolts, for
certain airplanes. For operators accomplishing the (follow-on)
repetitive ultrasonic inspections, that action proposed to require
replacement of the control rod with a new control rod manufactured
after June 1983; this replacement would constitute terminating action
for the repetitive inspections.
Interested persons have been afforded an opportunity to participate
in the making of this amendment. Due consideration has been given to
the comments received.
Request To Add a Visual Inspection
One commenter requests that the FAA revise paragraph (a)(2)(i) of
the proposal to require a visual inspection to detect cracks of the
control rods, prior to further flight, rather than the proposed
ultrasonic inspection. The commenter suggests that the proposed
ultrasonic inspection be accomplished within 300 flight hours following
accomplishment of the visual inspection. The commenter points out that
the control rods currently are being inspected ultrasonically at 2,000
flight cycles/15-month intervals in accordance with AD 90-20-16. Since
the ultrasonic inspections will identify cracks prior to rod failure,
the commenter states that it is unnecessary to accomplish an additional
ultrasonic inspection.
The FAA finds that clarification is necessary. Paragraph (a)(2)(i)
of this AD merely restates the existing requirements of paragraph A.2.
of AD 90-20-16. Therefore, for operators who have previously
accomplished at least the initial ultrasonic inspection in accordance
with AD 90-20-16, paragraph (a)(2)(i) of this AD requires that the next
scheduled inspection be performed within 2,000 landings or 15 months,
whichever occurs first, after the last inspection performed in
accordance with paragraph A.2. of AD 90-20-16. In light of this, the
FAA finds that the addition of a visual inspection, as suggested by the
commenter, is unnecessary. NOTE 2 has been added to this final rule to
clarify the restatement
[[Page 35939]]
of the existing requirements of AD 90-20-16.
Request To Include Reference to Additional Service Bulletins
Two commenters request that the FAA revise paragraph (a)(2)(ii) of
the proposed rule to reference Revision 2 of Boeing Service Bulletin
767-57-0021, dated July 26, 1990, as an additional source of service
information for accomplishment of the replacement. One of the
commenters points out that this will eliminate unnecessary processing
of an alternative method of compliance.
The FAA concurs partially. The FAA has determined that the
procedures for replacement of the control rod, specified in Revision 2
of Boeing Service Bulletin 767-57-0021, are identical to those
procedures in Revision 5 of the service bulletin (which is referenced
in the AD as the appropriate source of service information). In
addition, the FAA has determined that Revision 3, dated June 20, 1991,
and Revision 4, dated March 19, 1992, of Boeing Service Bulletin 767-
57-0021 also contain these identical replacement procedures. The FAA
has revised the final rule by adding a new NOTE 2 to clarify that
accomplishment of the replacement in accordance with Revision 2,
Revision 3, or Revision 4 of Service Bulletin 767-57-0021, is
considered acceptable for compliance with paragraph (a)(2)(ii) of the
AD. In addition, since paragraph (b) of the final rule also contains
these identical replacement procedures, the FAA has also added a
similar Note 3 to that paragraph.
Request To Correct Referenced Service Bulletin Number
One commenter notes that the service bulletin number referenced in
paragraph (b) of the proposal should be corrected to 767-57-0021. The
FAA acknowledges that it inadvertently referenced the incorrect service
bulletin number (i.e., 767-57-0221) in paragraph (b) of the proposal.
Therefore, the FAA has revised paragraph (b) of the final rule to
reference service bulletin number 767-57-0021.
Request for Assurance of Parts Availability
Two commenters support the rule, but question whether the
manufacturer of the control rod assemblies can produce the quantity of
required parts within the proposed compliance time.
The FAA has contacted to the manufacturer who has advised that
ample parts are currently available; therefore, obtaining them within
the required compliance time should not pose a problem for any affected
operator. However, under the provisions of paragraph (c) of the final
rule, the FAA may approve requests for adjustments to the compliance
time if data are submitted to substantiate that such an adjustment
would provide an acceptable level of safety.
Conclusion
After careful review of the available data, including the comments
noted above, the FAA has determined that air safety and the public
interest require the adoption of the rule with the changes previously
described. The FAA has determined that these changes will neither
increase the economic burden on any operator nor increase the scope of
the AD.
Cost Impact
There are approximately 271 Boeing Model 767 series airplanes of
the affected design in the worldwide fleet. The FAA estimates that 193
airplanes of U.S. registry will be affected by this proposed AD.
The actions that are currently required by AD 90-20-16 take
approximately 21 work hours per airplane to accomplish, at an average
labor rate of $60 per work hour. Required parts cost approximately
$5,500 per airplane. Based on these figures, the cost impact on U.S.
operators of the actions currently required is estimated to be
$1,304,680, or $6,760 per airplane.
For certain affected airplanes, the new replacement (terminating)
action that is required by this new AD will take approximately 1 work
hour per airplane to accomplish, at an average labor rate of $60 per
work hour. The cost of the required replacement parts is estimated to
be $5,500 per airplane. Based on these figures, the cost impact on U.S.
operators of the new requirements of this AD is estimated to be $5,560
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, or 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 removing amendment 39-6726 (55 FR
37858, September 14, 1990), and by adding a new airworthiness directive
(AD), amendment 39-9687, to read as follows:
96-14-05 Boeing: Amendment 39-9687. Docket 95-NM-124-AD. Supersedes
AD 90-20-16, Amendment 39-6726.
Applicability: Model 767 series airplanes; as listed in Boeing
Service Bulletin 767-57-0021, Revision 1, dated September 14, 1989,
or Revision 5, dated June 15, 1995; 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 (c) 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
[[Page 35940]]
been eliminated, the request should include specific proposed
actions to address it.
Compliance: Required as indicated, unless accomplished
previously.
Note 2: Paragraphs (a), (a)(1), (a)(1), (a)(2), and (a)(2)(i) of
this AD merely restate the initial and repetitive inspections
contained in paragraphs A.1. and A.2. of AD 90-20-16, amendment 39-
6726. Therefore, for operators who have previously accomplished at
least the initial inspection in accordance with AD 90-20-16,
paragraph (a)(2)(i) of this AD requires that the next scheduled
inspection be performed within 2,000 landings or within 15 months,
whichever occurs first, after the last inspection performed in
accordance with paragraph A.2. of AD 90-20-16.
To prevent loss of the pilot's ability to control the affected
slat, which could adversely affect the controllability of the
airplane, accomplish the following:
(a) For airplanes having line positions 1 through 235 inclusive:
Within the next 1,200 landings or 9 months after October 23, 1990
(the effective date of AD 90-20-16, amendment 39-6726), whichever
occurs first, unless accomplished within the last 800 landings or 6
months, whichever occurs later, perform a visual inspection to
determine the date of manufacture of the control rods of the
outboard leading edge slat of the wings, in accordance with the
Accomplishment Instructions of Boeing Service Bulletin 767-57-0021,
dated August 25, 1988; Revision 1, dated September 14, 1989;
Revision 2, dated July 26, 1990; or Revision 5, dated June 15, 1995.
(1) If the date of manufacture (stamped on the control rod) is
June 1983 or later, no further action is required by this paragraph.
(2) If the date of manufacture is illegible or is prior to June
1983, accomplish paragraphs (a)(2)(i) and (a)(2)(ii) of this AD.
(i) Prior to further flight, perform an ultrasonic inspection to
detect cracks of the control rods in accordance with Figure 1 of
Boeing Service Bulletin 767-57-0021, dated August 25, 1988, Revision
1, dated September 14, 1989, or Revision 2, dated July 26, 1990. If
any crack or fracture is detected, prior to further flight, replace
it in accordance with Figure 2 of the service bulletin. Repeat the
ultrasonic inspection of the control rods manufactured prior to June
1983 thereafter at intervals not to exceed 2,000 landings or 15
months, whichever occurs first, until the replacement required by
paragraph (a)(2)(ii) of this AD is accomplished.
(ii) Within 3,000 flight hours or 15 months after the effective
date of this AD, whichever occurs later, replace the control rod
with a new rod manufactured June 1983 or later, in accordance with
Boeing Service Bulletin 767-57-0021, Revision 5, dated June 15,
1995. Accomplishment of this replacement constitutes terminating
action for the repetitive inspection requirement of paragraph
(a)(2)(i) of this AD.
Note 3: Replacement accomplished prior to the effective date of
this amendment in accordance with Boeing Service Bulletin 767-57-
0021, Revision 2, dated July 26, 1990; Revision 3, dated June 20,
1991, or Revision 4, dated March 19, 1992; is considered acceptable
for compliance with paragraph (a)(2)(ii) of this AD.
(b) For airplanes having line number 1 through 264 inclusive,
and 266 through 273 inclusive: Within the next 2,500 landings or 18
months after October 23, 1990 (the effective date of AD 90-20-16,
amendment 39-6726, whichever occurs first, replace the control rod
end and attach bolt with a new configuration control rod end and
attach bolt on each wing, in accordance with Boeing Service Bulletin
767-57-0021, Revision 1, dated September 14, 1989; Revision 2, dated
July 26, 1990; or Revision 5, dated June 15, 1995.
Note 4: Replacement accomplished prior to the effective date of
this amendment in accordance with Boeing Service Bulletin 767-57-
0021, Revision 3, dated June 20, 1991, or Revision 4, dated March
19, 1992, is considered acceptable for compliance with paragraph (b)
of this AD.
(c) 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, Transport Airplane Directorate. 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 5: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Seattle ACO.
(d) 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.
(e) The inspections and replacements shall be done in accordance
with Boeing Service Bulletin 767-57-0021, dated August 25, 1988;
Boeing Service Bulletin 767-57-0021, Revision 1, dated September 14,
1989; Boeing Service Bulletin 767-57-0021, Revision 2, dated July
26, 1990; Boeing Service Bulletin 767-57-0021, Revision 3, dated
June 20, 1991; Boeing Service Bulletin 767-57-0021, Revision 4,
dated March 19, 1992; or Boeing Service Bulletin 767-57-0021,
Revision 5, dated June 15, 1995. 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.
(f) This amendment becomes effective on August 13, 1996.
Issued in Renton, Washington, on June 27, 1996.
S.R. Miller,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 96-16950 Filed 7-8-96; 8:45 am]
BILLING CODE 4910-13-P
