[Federal Register Volume 64, Number 191 (Monday, October 4, 1999)]
[Rules and Regulations]
[Pages 53621-53623]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-25218]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 98-NM-277-AD; Amendment 39-11339; AD 99-20-09]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 747 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 747 series airplanes, that
currently requires inspections of the lower engine mount to determine
if the tangential link upper bolt and nut are oriented properly, and if
the tangential link upper bolt nut is torqued within certain limits.
Additionally, that amendment requires replacement of the bolt and nut
with serviceable parts, if necessary, and requires certain follow-on
actions for airplanes on which the upper bolt is missing. This
amendment requires accomplishment of a previously optional terminating
action or a new alternative terminating action for the repetitive
inspections. This amendment is prompted by development of a new
terminating action by the manufacturer. The actions specified by this
AD are intended to prevent separation of the engine from the airplane
due to migration of the tangential link upper bolt.
DATES: Effective November 8, 1999.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of November 8, 1999.
The incorporation by reference of Boeing Alert Service Bulletin
747-71A2277, dated November 29, 1995, listed in the regulations, was
approved previously by the Director of the Federal Register as of
February 16, 1996 (61 FR 10270, March 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: Tamara L. Anderson, Aerospace
Engineer, Airframe Branch, ANM-120S, FAA, Transport Airplane
Directorate, Seattle Aircraft Certification Office, 1601 Lind Avenue,
SW., Renton, Washington 98055-4056; telephone (425) 227-2771; fax (425)
227-1181.
SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal
Aviation Regulations (14 CFR part 39) by superseding AD 96-03-01 R1,
amendment 39-9538 (61 FR 10270, March 13, 1996), which is applicable to
certain Boeing Model 747 series airplanes, was published in the Federal
Register on July 16, 1999 (64 FR 38379). The action proposed to
continue to require inspections of the lower engine mount to determine
if the tangential link upper bolt and nut are oriented properly, and if
the tangential link upper bolt nut is torqued within certain limits.
Additionally, that action also proposed to continue to require
replacement of the bolt and nut with serviceable parts, if necessary,
and requires certain follow-on actions for airplanes on which the upper
bolt is missing. That action also proposed to require accomplishment of
either a previously optional terminating action or a new, alternative
terminating action for the repetitive inspections.
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 commenter supports 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 421 airplanes of the affected design in the
worldwide fleet. The FAA estimates that 185 airplanes of U.S. registry
will be affected by this AD.
The inspections that are currently required by AD 96-03-01 R1 take
approximately 16 work hours per airplane to accomplish, at an average
labor rate of $60 per work hour. Based on these figures, the cost
impact of the currently required actions on U.S. operators is estimated
to be $177,600, or $960 per airplane, per inspection cycle.
The replacement of the safety link that is required as one option
for compliance with this AD action will take approximately 18 work
hours per airplane to accomplish, at an average
[[Page 53622]]
labor rate of $60 per work hour. Required parts will cost approximately
$30,228 per airplane. Based on these figures, the cost impact of this
replacement required by this AD on U.S. operators is estimated to be
$31,308 per airplane.
In lieu of replacement of the safety link, this AD provides for
replacement of the tangential link upper bolt on the aft engine mount
with a reworked bolt and a new nut retainer. Such replacement, which is
provided as an additional option for compliance with this AD action,
will take approximately 20 work hours per airplane to accomplish, at an
average labor rate of $60 per work hour. Required parts will cost
approximately $1,888 per airplane. Based on these figures, the cost
impact of this replacement required by this AD on U.S. operators is
estimated to be $3,088 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 removing amendment 39-9538 (61 FR
10270, March 13, 1996), and by adding a new airworthiness directive
(AD), amendment 39-11339, to read as follows:
99-20-09 Boeing: Amendment 39-11339. Docket 98-NM-277-AD. Supersedes
AD 96-03-01 R1, amendment 39-9538.
Applicability: Model 747 series airplanes, as listed in Boeing
Alert Service Bulletin 747-71A2277, dated November 29, 1995; or
Boeing Service Bulletin 747-71A2277, Revision 1, dated May 21, 1998,
or Revision 2, dated January 14, 1999; 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)(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 separation of the engine from the airplane,
accomplish the following:
Restatement of Requirements of AD 96-03-01 R1, Amendment 39-9538
Inspections and Corrective Actions
(a) Within 90 days after February 16, 1996 (the effective date
of AD 96-03-01 R1, amendment 39-9538), accomplish the requirements
of paragraphs (a)(1) and (a)(2) of this AD in accordance with Boeing
Alert Service Bulletin 747-71A2277, dated November 29, 1995, or
Boeing Service Bulletin 747-71A2277, Revision 1, dated May 21, 1998,
or Revision 2, dated January 14, 1999.
(1) Perform a visual inspection to ensure that installation of
the tangential link upper bolt nut is on the forward side of the
engine mount fitting.
(i) If the tangential link upper bolt nut is installed on the
forward side of the engine mount fitting, repeat the visual
inspection at intervals not to exceed 18 months.
(ii) If the tangential link upper bolt nut is not installed on
the forward side of the engine mount fitting, prior to further
flight, remove the nut, bolt, and washers, and reinstall the nut,
bolt, and washers in accordance with the service bulletin.
Thereafter, repeat the visual inspection at intervals not to exceed
18 months.
(iii) If the tangential link upper bolt is missing from the
engine mount fitting, prior to further flight, perform the various
follow-on actions in accordance with the service bulletin. (The
follow-on actions include visual inspections, magnetic particle
inspections, replacement of the lower engine mount fitting with a
serviceable part, if necessary; installation of new safety links,
bolts, and nuts; and installation of a new tangential link upper
bolt.) Thereafter, repeat the visual inspection at intervals not to
exceed 18 months.
(2) Perform an inspection to verify that the torque value of the
tangential link upper bolt (on both sides of the mount) is within
the limits specified in the service bulletin.
(i) If the torque value of the tangential link upper bolt nut is
within the limits specified in the service bulletin, repeat the
inspection (verification) at intervals not to exceed 18 months.
(ii) If the torque value of the tangential link upper bolt nut
is outside the limits specified in the service bulletin, prior to
further flight, perform a visual inspection of the tangential link
upper bolt and washer for any damage or discrepancy, in accordance
with the service bulletin.
(A) If no damage or discrepancy of the tangential link upper
bolt and washers is found, prior to further flight, replace the bolt
nut with a new or serviceable part in accordance with the service
bulletin. Thereafter, repeat the inspection (verification) specified
in paragraph (a)(2) of this AD at intervals not to exceed 18 months.
(B) If any damage or discrepancy of the tangential link upper
bolt and washers is found, prior to further flight, replace the
damaged or discrepant part with a new or serviceable part, and
replace the bolt nut with a new or serviceable part, in accordance
with the service bulletin. Thereafter, repeat the inspection
(verification) specified in paragraph (a)(2) of this AD at intervals
not to exceed 18 months.
New Requirements of This AD
Replacement
(b) Within 18 months after the effective date of this AD,
accomplish the requirements of either paragraph (b)(1) or (b)(2) of
this AD. Accomplishment of either paragraph (b)(1) or (b)(2) of this
AD constitutes terminating action for the repetitive inspection
requirements of this AD.
(1) Replace the safety links on the aft engine mount with
modified safety links in accordance with Boeing Service Bulletin
747-71-2206, dated April 16, 1987; or Boeing Service Bulletin 747-
71-2206, Revision 1, dated November 12, 1987, as revised by Boeing
Notice of Status Change No. 747-71-2206 NSC 1, dated December 4,
1987, and Boeing Notice of Status Change
[[Page 53623]]
No. 747-71-2206 NSC 2, dated March 17, 1988.
(2) Replace the tangential link upper bolt on the aft engine
mount with a reworked bolt and a new nut retainer, in accordance
with Parts 2 and 3 of Boeing Service Bulletin 747-71A2277, Revision
1, dated May 21, 1998, or Revision 2, dated January 14, 1999.
Alternative Methods of Compliance
(c)(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 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.
(c)(2) Alternative methods of compliance, approved previously in
accordance with AD 96-03-01 R1, amendment 39-9538, are approved as
alternative methods of compliance with this AD.
Note 2: 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
(d) 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
(e) The actions shall be done in accordance with Boeing Alert
Service Bulletin 747-71A2277, dated November 29, 1995; Boeing
Service Bulletin 747-71A2277, Revision 1, dated May 21, 1998; Boeing
Service Bulletin 747-71A2277, Revision 2, dated January 14, 1999;
Boeing Service Bulletin 747-71-2206, dated April 16, 1987; or Boeing
Service Bulletin 747-71-2206, Revision 1, dated November 12, 1987,
as revised by Boeing Notice of Status Change No. 747-71-2206 NSC 1,
dated December 4, 1987, and Boeing Notice of Status Change No. 747-
71-2206 NSC 2, dated March 17, 1988; as applicable.
(1) The incorporation by reference of Boeing Service Bulletin
747-71A2277, Revision 2, dated January 14, 1999; Boeing Service
Bulletin 747-71-2206, dated April 16, 1987; or Boeing Service
Bulletin 747-71-2206, Revision 1, dated November 12, 1987, as
revised by Boeing Notice of Status Change No. 747-71-2206 NSC 1,
dated December 4, 1987, and Boeing Notice of Status Change No. 747-
71-2206 NSC 2, dated March 17, 1988; as applicable is approved by
the Director of the Federal Register in accordance with 5 U.S.C.
552(a) and 1 CFR part 51. Boeing Service Bulletin 747-71-2206,
Revision 1, dated November 12, 1987, contains the following list of
effective pages:
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Revision level
Page No. shown on page Date shown on page
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1-5, 9, 10, 12.............. 1.............. November 12, 1987.
6-8, 11, 13-18.............. Original....... April 16, 1987.
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(2) The incorporation by reference of Boeing Alert Service
Bulletin 747-71A2277, dated November 29, 1995, was approved
previously by the Director of the Federal Register as of February
16, 1996 (61 FR 10270, March 13, 1996).
(3) 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 November 8, 1999.
Issued in Renton, Washington, on September 22, 1999.
D.L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 99-25218 Filed 10-1-99; 8:45 am]
BILLING CODE 4910-13-P
