[Federal Register Volume 65, Number 54 (Monday, March 20, 2000)]
[Rules and Regulations]
[Pages 14848-14850]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 00-6157]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 99-NM-73-AD; Amendment 39-11629; AD 2000-05-19]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 727 Series Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule.
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[[Page 14849]]
SUMMARY: This amendment adopts a new airworthiness directive (AD),
applicable to all Boeing Model 727 series airplanes, that requires a
one-time detailed visual inspection of the fuselage skin and bonded
doubler area above the forward entry doorway to detect fatigue cracking
or the existence of certain repairs, and follow-on corrective actions,
if necessary. This action also requires a preventive modification or
full-sized repair doubler, as applicable. This amendment is prompted by
reports of fatigue cracking in the fuselage skin and bonded doublers in
the forward and aft corners above the forward entry doorway. The
actions specified by this AD are intended to prevent such fatigue
cracking of the fuselage skin and bonded doubler, which could result in
reduced structural integrity and consequent loss of cabin
pressurization.
DATES: Effective April 24, 2000.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of April 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: Walter Sippel, Aerospace Engineer,
Airframe Branch, ANM-120S, FAA, Transport Airplane Directorate, Seattle
Aircraft Certification Office, 1601 Lind Avenue, SW., Renton,
Washington 98055-4056; telephone (425) 227-2774; 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 all Boeing Model 727 series
airplanes was published in the Federal Register on December 7, 1999 (64
FR 68297). That action proposed to require a one-time detailed visual
inspection of the fuselage skin and bonded doubler area above the
forward entry doorway to detect fatigue cracking or the existence of
certain repairs, and follow-on corrective actions, if necessary. That
action also proposed to require a preventive modification or full-sized
repair doubler, as applicable.
Comments
Interested persons have been afforded an opportunity to participate
in the making of this amendment. Due consideration has been given to
the comments received.
One commenter supports the proposed rule. Another commenter states
that it is not affected by the proposed rule.
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 as proposed.
Cost Impact
There are approximately 1,429 airplanes of the affected design in
the worldwide fleet. The FAA estimates that 887 airplanes of U.S.
registry will be affected by this AD.
The FAA estimates that it will take approximately 1 work hour per
airplane to accomplish the inspection of the fuselage skin and bonded
doubler area, and that the average labor rate is $60 per work hour.
Based on these figures, the cost impact of the AD on U.S. operators is
estimated to be $53,220, or $60 per airplane.
The FAA estimates that it will take approximately 27 work hours per
airplane to accomplish the preventive modification or full-sized repair
doubler, and that the average labor rate is $60 per work hour. Required
parts will cost approximately $979 per airplane. Based on these
figures, the cost impact of the AD on U.S. operators is estimated to be
$2,305,313, or $2,599 per airplane.
The cost impact figures discussed above are based on assumptions
that no operator has yet accomplished any of the proposed 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 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:
2000-05-19 Boeing: Amendment 39-11629. Docket 99-NM-73-AD.
Applicability: All Model 727 series airplanes, 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 been
eliminated, the request should include specific proposed actions to
address it.
Compliance: Required as indicated, unless accomplished
previously.
To prevent fatigue cracking of the fuselage skin and bonded
doubler area above the forward entry doorway, which could result in
reduced structural integrity and consequent loss of cabin
pressurization, accomplish the following:
Detailed Visual Inspection
(a) Prior to the accumulation of 60,000 total flight cycles, or
within 3,000 flight cycles after the effective date of this AD,
whichever occurs later: Perform a one-time detailed visual
inspection of the fuselage skin and
[[Page 14850]]
bonded doubler area above the forward entry doorway to detect
fatigue cracking or the existence of a previous repair, in
accordance with Boeing Service Bulletin 727-53-0186, Revision 1,
dated May 21, 1992.
Corrective Action
(1) If no crack or repair is detected, prior to further flight,
perform the preventive modification in accordance with the service
bulletin. No further action is required by this AD.
(2) If any crack but no repair is detected, prior to further
flight, accomplish the actions required by paragraph (a)(2)(i),
(a)(2)(ii), or (a)(2)(iii), as applicable.
(i) If any crack is less than or equal to 2.5 inches, perform
the full-sized repair doubler in accordance with Boeing Service
Bulletin 727-53-0186, Revision 1, dated May 21, 1992. Accomplishment
of this action constitutes terminating action for the requirements
of this AD.
(ii) If any crack exceeds 2.5 inches, repair in accordance with
a method approved by the Manager, Seattle Aircraft Certification
Office (ACO), FAA, Transport Airplane Directorate; or in accordance
with data meeting the type certification basis of the airplane
approved by a Boeing Company Designated Engineering Representative
(DER) who has been authorized by the Manager, Seattle ACO, to make
such findings. For a repair method to be approved by the Manager,
Seattle ACO, or the Boeing DER, as required by this paragraph, the
approval letter must specifically reference this AD.
(iii) If any crack in the bear strap is detected, repair in
accordance with a method approved by the Manager, Seattle ACO; or in
accordance with data meeting the type certification basis of the
airplane approved by a Boeing Company DER who has been authorized by
the Manager, Seattle ACO, to make such findings. For a repair method
to be approved by the Manager, Seattle ACO, or the Boeing DER, as
required by this paragraph, the approval letter must specifically
reference this AD.
(3) If any repair is found, accomplish paragraph (a)(3)(i),
(a)(3)(ii), or (a)(3)(iii), of this AD, as applicable.
(i) If a full-sized repair doubler is found, as specified by
Boeing Service Bulletin 727-53-0186, dated April 27, 1989, or
Revision 1, dated May 21, 1992, and any crack is less than or equal
to 2.5 inches, no further action is required by this AD.
(ii) If a half-sized repair doubler is found, as specified by
Boeing Service Bulletin 727-53-0186, dated April 27, 1989, or
Revision 1, dated May 21, 1992, and any crack is less than or equal
to 2.5 inches and is not in the bear strap: Prior to further flight,
perform the full-sized repair doubler in accordance with Boeing
Service Bulletin 727-53-0186, Revision 1, dated May 21, 1992. No
further action is required by this AD.
(iii) If a half-sized or full-sized repair doubler is found, as
specified by the service bulletin, and any crack exceeds 2.5 inches
or is located in the bear strap: Prior to further flight, repair in
accordance with a method approved by the Manager, Seattle ACO or in
accordance with data meeting the type certification basis of the
airplane approved by a Boeing Company DER who has been authorized by
the Manager, Seattle ACO, to make such findings. For a repair method
to be approved by the Manager, Seattle ACO, or the Boeing DER, as
required by this paragraph, the approval letter must specifically
reference this AD.
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.''
Terminating Action for AD 94-05-04
(b) Accomplishment of the requirements of this AD constitutes
terminating action for the requirements of paragraph (a) of AD 94-
05-04, amendment 39-8842 (which are required to be accomplished in
accordance with Appendices A.3, B.3, and C.3 of Boeing Document
Number D6-54860, ``Aging Airplane Service Bulletin Structural
Modification and Inspection Program--Model 727,'' Revision G, dated
March 5, 1993), with respect to the modification specified in Boeing
Service Bulletin 727-53-0186, dated April 27, 1989. All other
service bulletins referenced in Boeing Document Number D6-54860
still apply.
Alternative Methods of Compliance
(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 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
(d) Special flight permits may be issued in accordance with
Sec. 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) Except as provided by paragraphs (a)(2)(ii), (a)(2)(iii),
and (a)(3)(iii) of this AD, the actions shall be done in accordance
with Boeing Service Bulletin 727-53-0186, Revision 1, dated May 21,
1992. 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 April 24, 2000.
Issued in Renton, Washington, on March 8, 2000.
Donald L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 00-6157 Filed 3-17-00; 8:45 am]
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